Airworthiness directives: Boeing,
[Federal Register: December 3, 2004 (Volume 69, Number 232)]
[Proposed Rules]
[Page 70204-70208]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03de04-11]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA-2004-19796; Directorate Identifier 2004-NM-61-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, -200B, -200C, -300, -400, and -400D Series Airplanes; and Model 747SR Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for certain Boeing Model 747 series airplanes. That AD currently requires a one-time inspection to determine the material type of the stop support fittings of the main entry doors (MEDs). That AD also currently requires repetitive detailed inspections to detect cracks of certain stop support fittings of the MEDs, and replacement of any cracked stop support fitting with a certain new stop support fitting. This proposed AD would add new inspections and replacement if necessary of the stop support fittings of MED 3, and add airplanes to the applicability. This proposed AD is prompted by reports of MED 3 having certain stop support fittings which are susceptible to stress corrosion cracking. We are proposing this AD to detect and correct stress corrosion cracking of the stop support fittings of the MEDs, which could result in damage to the adjacent forward edge frame of the door and consequent loss of a MED and rapid decompression of the airplane.
DATES: We must receive comments on this proposed AD by January 18, 2005.
ADDRESSES: Use one of the following addresses to submit comments on this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking web site: Go to http://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124- 2207.
You can examine the contents of this AD docket on the Internet at http://dms.dot.gov, or at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401, on the plaza level of the Nassif Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Technical information: Ivan Li, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056;
[[Page 70205]]
telephone (425) 917-6437; fax (425) 917-6590.
Plain language information: Marcia Walters, marcia.walters@faa.gov.
SUPPLEMENTARY INFORMATION:
Docket Management System (DMS)
The FAA has implemented new procedures for maintaining AD dockets electronically. As of May 17, 2004, new AD actions are posted on DMS and assigned a docket number. We track each action and assign a corresponding directorate identifier. The DMS AD docket number is in the form ``Docket No. FAA-2004-99999.'' The Transport Airplane Directorate identifier is in the form ``Directorate Identifier 2004-NM- 999-AD.'' Each DMS AD docket also lists the directorate identifier (``Old Docket Number'') as a cross-reference for searching purposes.
Comments Invited
We invite you to submit any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ``Docket No. FAA-2004-19796; Directorate Identifier 2004-NM-61-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov , including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov.
We are reviewing the writing style we currently use in regulatory documents. We are interested in your comments on whether the style of this document is clear, and your suggestions to improve the clarity of our communications that affect you. You can get more information about plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.Examining the Docket
You can examine the AD docket in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647-5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them.
Discussion
On December 14, 1998, we issued AD 98-26-13, amendment 39-10954 (63 FR 70316, December 21, 1998), for certain Boeing Model 747-100, -100B, -200, -200B, -200C, -300, -400, and 747SR series airplanes having line numbers 1 through 830 inclusive. That AD requires a one-time inspection to determine the material type of the stop support fittings of the main entry doors (MEDs). That AD also currently requires repetitive detailed inspections to detect cracks of certain stop support fittings of the MEDs, and replacement of any cracked stop support fitting with a certain new stop support fitting. That AD was prompted by reports that stress corrosion cracking was found on certain stop support fittings of the MEDs. We issued that AD to detect and correct stress corrosion cracking of the stop support fittings of the MEDs, which could lead to failure of the stop support fittings, consequent loss of a MED, and rapid decompression of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 98-26-13, we received a report from the manufacturer that the new stop support fittings installed in production for MED 3 on airplanes after line number 830 may not have been made of the correct material type. In addition, the new stop support fittings supplied by Boeing as the replacement fitting for MED 3 may not have been made from the correct material type.
Relevant Service Information
We have reviewed Boeing Special Attention Service Bulletin 747-53- 2485, dated January 8, 2004. The service bulletin describes procedures for performing a high frequency eddy current (HFEC) inspection to determine the material type of the stop support fittings of MED 3. The service bulletin also describes procedures for repetitive visual inspections to detect cracks of the stop support fittings (not made from 7075-T73 or 7050-T7451 material) of MED 3, and replacement of any cracked fitting with a new fitting made from 7075-T73 or 7050-T7451 material. In addition, the service bulletin describes procedures for optional replacement of the stop support fittings of the MEDs with stop support fittings made from 7075-T73 or 7050-T7451 material, which would eliminate the need for repetitive inspections. The new stop support fitting is less susceptible to stress corrosion cracking.
The FAA has reviewed Boeing Service Bulletin 747-53-2358, Revision 1, dated April 19, 2001 (the original issue, dated August 26, 1993, is referenced as the appropriate source of service information for accomplishing AD 98-26-13). Revision 1 of the service bulletin describes procedures for performing an HFEC inspection to determine the material type of the stop support fittings of the MEDs. The service bulletin also describes procedures for repetitive visual inspections to detect cracks of the stop support fitting (not made from 7075-T73 or 7050-T7451 material) of the MEDs, and replacement of any cracked fitting with a new fitting made from 7075-T73 or 7050-T7451 material. In addition, the service bulletin describes procedures for optional replacement of the stop support fittings of the MEDs with stop support fittings made from 7075-T73 or 7050-T7451 material, which would eliminate the need for repetitive inspections. The new stop support fitting is less susceptible to stress corrosion cracking.
We have determined that accomplishment of the actions specified in the service information will adequately address the unsafe condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. Therefore, we are proposing this AD, which would supersede AD 98-26-13. This proposed AD would continue to require a one-time inspection to determine the material type of the stop support fittings of the MEDs. This proposed AD would also continue to require repetitive detailed inspections to detect cracks of certain stop support fittings of the MEDs, and replacement of any cracked stop support fitting with a certain new stop support fitting. This proposed AD would also require new inspections and replacement if necessary of the stop support fittings of MED 3 and add airplanes to the applicability. This proposed AD would require you to use the service information described
[[Page 70206]]
previously to perform these actions, except as discussed under ``Differences Between the Proposed AD and Service Bulletins.''
Differences Between the Proposed AD and Service Bulletins
For certain airplanes, Boeing Special Attention Service Bulletin 747-53-2485, dated January 8, 2004, specifies an inspection threshold of 6 years after the airplane was delivered or 18 months since the release of the service bulletin, whichever occurs later. However, for these same airplanes, paragraph (i) of the proposed AD specifies an inspection threshold of 72 months after the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, or 18 months after the effective date of the AD, whichever occurs later. This decision is based on our determination that the date the airplane was delivered may be interpreted differently by different operators. We find that our proposed terminology is generally understood within the industry and records will always exist that establish these dates with certainty.
Whereas Boeing Service Bulletin 747-53-2358, dated August 26, 1993; and Boeing Service Bulletin 747-53-2358, Revision 1, dated April 19, 2001; specify a ``visual inspection,'' the intent of the proposed AD is to require a ``detailed inspection.'' Additionally, a note has been added to the proposed AD to define that inspection.
Explanation of Change to Applicability
We have revised the applicability of the existing AD to identify model designations as published in the most recent type certificate data sheet for the affected models. In paragraphs (f) and (g) of the proposed AD, the model designation ``747-100B SUD'' has been added. There is no increase in the number of applicable airplanes for these paragraphs.
Clarification of Inspection Type
Although Boeing Special Attention Service Bulletin 747-53-2485, dated January 8, 2004, specifies a ``detailed visual inspection,'' this proposed AD requires a ``detailed inspection.''
Clarification of Service Bulletin
Operators should also note that Boeing Service Bulletin 747-53- 2358, Revision 1, dated April 19, 2001, specifies in the ``Action'' and ``Description'' paragraphs that you can end the repetitive inspections if you replace the stop support fittings with stop support fittings made from 7075-T73 or 7050-T7451 material. However, the Note under ``Stop Support Fitting Replacement'' of the Work Instructions of the service bulletin only specifies ending repetitive inspections if you replace with stop support fittings made from 7075-T73. Replacing with stop support fittings made of 7075-T73 or 7050-T7451 material does end the repetitive inspections as both are less susceptible to stress corrosion cracking.
Change to the Number of Airplanes in the Costs of Compliance
Operators should note that for AD 98-26-13 we estimated that there are about 575 airplanes of the affected design in the worldwide fleet and that about 164 airplanes of U.S. registry would be affected by that AD. However, for this proposed AD, which includes actions required by AD 98-26-13, we estimate that there are 814 airplanes of the affected design in the worldwide fleet and that 119 airplanes of U.S. registry would be affected by the proposed AD. The increase in the number of airplanes worldwide is due to the expanded applicability. The decrease in number of airplanes of U.S. registry may be due to a number of reasons such as retirement of airplanes and transfer of airplanes to foreign operators.
Change to Existing AD
This proposed AD would retain all requirements of AD 98-26-13. Since AD 98-26-13 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table:
Revised Paragraph Identifiers
Corresponding requirement in Requirement in AD 98-26-13
this proposed AD
Paragraph (a).......................... Paragraph (f). Paragraph (b).......................... Paragraph (g). Paragraph (c).......................... Paragraph (l).
Costs of Compliance
There are about 814 airplanes of the affected design in the worldwide fleet. There are about 119 airplanes of U.S. registry that would be affected by this proposed AD. The following table provides the estimated costs for U.S. operators to comply with this proposed AD.
Estimated Costs
Average Action
Work hours labor rate Parts Cost per per hour
door
HFEC Inspection (required by AD 98-26-13)...................
1
$65
None
$65 Detailed Inspection as applicable (required by AD 98-26-13).
2
65
None
130 Optional Terminating Action (specified in AD 98-26-13)......
124
65 $13,000 21,060 Detailed Inspection and HFEC Inspection as applicable (new
3
65
None
195 proposed action)........................................... Replacement as applicable (new proposed action).............
120
65 17,724 25,524
Authority for This Rulemaking
The FAA's authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. Subtitle I, Section 106 describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the agency's authority.
This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, the FAA is charged with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this proposed AD.
Regulatory Findings
We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and
[[Page 70207]]
responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed regulation:
-
Is not a ``significant regulatory action'' under Executive Order 12866;
-
Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and
-
Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
-
The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
-
The FAA amends Sec. 39.13 by removing amendment 39-10954 (63 FR 70316, December 21, 1998) and adding the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2004-19796; Directorate Identifier 2004-NM- 61-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on this airworthiness directive (AD) action by January 18, 2005.
Affected ADs
(b) This AD supersedes AD 98-26-13, amendment 39-10954.
Applicability
(c) This AD applies to Boeing Model 747-100, -100B, -100B SUD, - 200B, -200C, -300, -400, and -400D series airplanes; and Model 747SR series airplanes; having line numbers 1 through 1301 inclusive; certificated in any category.
Unsafe Condition
(d) This AD was prompted by reports of main entry door (MED) 3 having certain stop support fittings which are susceptible to stress corrosion cracking. We are issuing this AD to detect and correct stress corrosion cracking of the stop support fittings of the MEDs which could result in damage to the adjacent forward edge frame of the door and consequent loss of a MED and rapid decompression of the airplane.
Compliance
(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Requirements of AD 98-26-13
Inspections and Corrective Action
(f) For Model 747-100, -100B, -100B SUD, -200, -200B, -200C, - 300, -400, and 747SR series airplanes having line numbers 1 through 830 inclusive: Within 18 months after January 25, 1999 (the effective date of AD 98-26-13, amendment 39-10954), perform a high frequency eddy current (HFEC) inspection to determine the material type of the stop support fittings of the MEDs, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53- 2358, dated August 26, 1993; or Boeing Service Bulletin 747-53-2358, Revision 1, dated April 19, 2001. Perform the inspection only at those locations where the material type of the stop support fittings is unknown, as specified in Figure 3, Table 1, of either service bulletin. As of the effective date of this AD, do the actions in accordance with Boeing Service Bulletin 747-53-2358, Revision 1, dated April 19, 2001.
(1) If the fitting is made from 7075-T73 or 7050-T7451 material, no further action is required by this AD for that fitting; however, the requirements of paragraph (l) of this AD still applies.
(2) If the fitting is not made from 7075-T73 or 7050-T7451 material, before further flight, perform a detailed inspection to detect cracks of the stop support fitting of the MEDs, in accordance with the applicable service bulletin.
Note 1: For the purposes of this AD, a detailed inspection is ``an intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required.''
(i) If no crack is detected, repeat the detailed inspection thereafter at intervals not to exceed 36 months or 2,000 flight cycles, whichever occurs first.
(ii) If any crack is detected, before further flight, replace the fitting with a stop support fitting made from 7075-T73 or 7050- T7451 material, in accordance with the applicable service bulletin.
(g) For Model 747-100, -100B, -100B SUD, -200, -200B, -200C, - 300, -400, and 747SR series airplanes having line numbers 1 through 830 inclusive: Replacement of the stop support fitting of the MEDs with a stop support fitting made from 7075-T73 material, in accordance with Boeing Service Bulletin 747-53-2358, dated August 26, 1993; or replacement with a stop support fitting made from 7075- T73 or 7050-T7451 material, in accordance with Boeing Service Bulletin 747-53-2358, Revision 1, dated April 19, 2001; constitutes terminating action for the repetitive inspection requirements of paragraph (f) of this AD for the replaced fitting. As of the effective date of this AD, only Boeing Service Bulletin 747-53-2358, Revision 1, dated April 19, 2001, may be used.
New Requirements of This AD
Inspection for Material Type
(h) For Model 747-100, -100B, -100B SUD, -200B, -200C, -300, - 400, and -400D series airplanes, and Model 747SR series airplanes, having line numbers 1 through 830 inclusive on which the actions specified in the Accomplishment Instructions of Boeing Service Bulletin 747-53-2358, dated August 26, 1993; or Boeing Service Bulletin 747-53-2358, Revision 1, dated April 19, 2001; have been done: Do the inspection specified in paragraph (h)(1) or (h)(2) of this AD, as applicable, at the time specified.
(1) Except as provided by paragraph (h)(2) of this AD, if any stop support fitting, 2L through 6L and 2R through 6R, of MED 3, was replaced before the effective date of this AD: Perform a one-time HFEC inspection to determine the material type of the stop support fittings of MED 3 that were replaced, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747-53-2485, dated January 8, 2004, at the later of the times specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD.
(i) Within 72 months after the stop support fitting of MED 3 was replaced.
(ii) Within 18 months after the effective date of this AD.
(2) If any stop support fitting, 2L through 6L and 2R through 6R, of MED 3, cannot be determined conclusively by reviewing airplane maintenance records that the fitting was not replaced, within 18 months after the effective date of this AD, perform a one- time HFEC inspection to determine the material type of the stop support fitting, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747-53-2485, dated January 8, 2004.
(i) For airplanes having line numbers 831 through 1301 inclusive: At the later of the times specified in paragraphs (i)(1) and (i)(2) of this AD, perform a one-time HFEC inspection to determine the material type of the stop support fittings of MED 3 in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747-53-2485, dated January 8, 2004.
(1) Before 72 months since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness.
(2) Within 18 months after the effective date of this AD.
No Further Action
(j) If, during any HFEC inspection required by paragraph (h) or (i) of this AD, any fitting is found to be made of 7075-T73 or 7050- T7451 material, no further action is required by this AD for that fitting; however, paragraph (l) of this AD still applies.
[[Page 70208]]
Initial and Repetitive Inspections for Cracking and Corrective Action
(k) If, during any HFEC inspection required by paragraph (h) or (i) of this AD, any fitting is found not to be made of 7075-T73 or 7050-T7451 material, before further flight, perform a detailed inspection for cracks of the fitting in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747-53-2485, dated January 8, 2004.
(1) If no crack is detected, repeat the detailed inspection specified in paragraph (k) of this AD thereafter at intervals not to exceed 36 months or 2,000 flight cycles, whichever comes first. Doing the replacement specified in paragraph (k)(2) of this AD ends the repetitive inspections for the replaced fitting.
(2) If any crack is detected, before further flight, replace the fitting with a fitting made of 7075-T73 or 7050-T7451 material in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747-53-2485, dated January 8, 2004. No further action is required by this AD for that fitting; however, paragraph (l) of this AD still applies.
Parts Installation
(l) As of the date specified in paragraph (l)(1) or (l)(2) of this AD, as applicable, no person shall install on any airplane a stop support fitting of the MEDs made from either 7079-T651 or 7075- T651 material.
(1) For airplanes having line numbers 1 through 830 inclusive: As of January 25, 1999.
(2) For airplanes having line numbers 831 through 1301 inclusive: As of the effective date of this AD.
Alternative Methods of Compliance (AMOCs)
(m)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.
(2) AMOCs, approved previously per AD 98-26-13, amendment 39- 10954, are approved as AMOCs with paragraph (f) or (g) of this AD, as applicable. However, any stop support fitting, 2L through 6L and 2R through 6R, of MED 3 that was replaced is still required to be inspected as required in paragraph (h) of this AD.
Issued in Renton, Washington, on November 26, 2004. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-26664 Filed 12-2-04; 8:45 am]
BILLING CODE 4910-13-P
