Airworthiness Directives; The Boeing Company Airplanes
Federal Register, Volume 83 Issue 27 (Thursday, February 8, 2018)
Federal Register Volume 83, Number 27 (Thursday, February 8, 2018)
Proposed Rules
Pages 5576-5579
From the Federal Register Online via the Government Publishing Office www.gpo.gov
FR Doc No: 2018-02085
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Docket No. FAA-2018-0031; Product Identifier 2017-NM-127-AD
RIN 2120-AA6417
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 727 airplanes. This proposed AD was prompted by significant changes made to the airworthiness limitations (AWLs) related to fuel tank ignition prevention. This proposed AD would require revising the maintenance or inspection program, as applicable, to incorporate the latest revision of the AWLs. We are proposing this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by March 26, 2018.
ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0031.
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0031; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Christopher Baker, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW, Renton, WA 98057-3356; phone: 425-917-6498; fax: 425-917-6590; email: email protected.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0031; Product Identifier 2017-NM-127-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM.
Discussion
The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a final rule titled ``Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements'' (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, that rule included Amendment 21-78, which established Special Federal Aviation Regulation No. 88 (``SFAR 88'') at 14 CFR part 21. Subsequently, SFAR 88 was amended by Amendment 21-82 (67 FR 57490, September 20, 2002; corrected at 67 FR 70809, November 26, 2002) and Amendment 21-83 (67 FR 72830, December 9, 2002; corrected at 68 FR 37735, June 25, 2003, to change ``21-72'' to ``21-83'').
Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the final rule published on May 7, 2001, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews.
In evaluating these design reviews, we have established four criteria intended
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to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, single failures in combination with another latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken that may mitigate the need for further action.
We have determined that the actions identified in this proposed AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing 727-100/200 Airworthiness Limitations (AWLs) D6-
8766-AWL, dated December 2016. The service information describes AWL tasks that include airworthiness limitation instructions (ALIs) and critical design configuration control limitations (CDCCLs) related to fuel tank ignition prevention. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section.
FAA's Determination
We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require revision of the maintenance or inspection program to incorporate the ALI and CDCCL tasks described previously.
This proposed AD would require revisions to certain operator maintenance documents to include new actions (e.g., inspections) and CDCCLs. Compliance with these actions and CDCCLs is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this proposed AD, the operator may not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (k) of this proposed AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane.
Notwithstanding any other maintenance or operational requirements, components that have been identified as airworthy or installed on the affected airplanes before accomplishing the revision of the airplane maintenance or inspection program specified in this proposed AD do not need to be reworked in accordance with the latest revision of the CDCCLs specified by this proposed AD for incorporation. However, once the airplane maintenance or inspection program has been revised as specified by this proposed AD, future maintenance actions on these components must be done in accordance with the CDCCLs specified by this proposed AD.
Related Rulemaking
Five ADs are related to this NPRM. We have determined that certain requirements of those ADs may be terminated when the referenced AWLs specified in this proposed AD have been incorporated, as follows:
The revision required by paragraph (g) of AD 2008-04-10 R1, Amendment 39-16121 (74 FR 66227, December 15, 2009).
The revision required by paragraph (h) of AD 2009-05-03, Amendment 39-15827 (74 FR 8851, February 27, 2009).
The revision required by paragraph (j) of AD 2011-12-05, Amendment 39-16712 (76 FR 33991, June 10, 2011).
The revision required by paragraph (h) of AD 2013-22-03, Amendment 39-17635 (78 FR 65193, October 31, 2013).
The revision required by paragraphs (n)(1) and (n)(2) of AD 2013-24-15, Amendment 39-17692 (78 FR 72791, December 4, 2013).
Differences Between This Proposed AD and the Service Information
AWL No. 28-AWL-03 identifies certain wire types. Paragraph (h)(1) of this proposed AD specifies additional acceptable wire types and cables.
AWL No. 28-AWL-03 identifies certain sleeving materials. Paragraph (h)(2) of this proposed AD specifies additional acceptable sleeving materials.
Costs of Compliance
We estimate that this proposed AD affects 20 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Maintenance or inspection program 1 work-hour x $85 per hour $0 $85 $1,700
revision. = $85.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. 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.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA 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 rulemaking action.
This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes and associated appliances to the Director of the System Oversight Division.
Regulatory Findings
We determined that this proposed AD would not have federalism implications
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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 responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed regulation:
(1) Is not a ``significant regulatory action'' under Executive Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, 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
0
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The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 Amended
0
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The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD):
The Boeing Company: Docket No. FAA-2018-0031; Product Identifier 2017-NM-127-AD.
(a) Comments Due Date
We must receive comments by March 26, 2018.
(b) Affected ADs
This AD affects the ADs specified in paragraphs (b)(1) through (b)(5) of this AD.
(1) AD 2008-04-10 R1, Amendment 39-16121 (74 FR 66227, December 15, 2009) (``AD 2008-04-10 R1'').
(2) AD 2009-05-03, Amendment 39-15827 (74 FR 8851, February 27, 2009) (``AD 2009-05-03'').
(3) AD 2011-12-05, Amendment 39-16712 (76 FR 33991, June 10, 2011) (``AD 2011-12-05'').
(4) AD 2013-22-03, Amendment 39-17635 (78 FR 65193, October 31, 2013) (``AD 2013-22-03'').
(5) AD 2013-24-15, Amendment 39-17692 (78 FR 72791, December 4, 2013) (``AD 2013-24-15'').
(c) Applicability
This AD applies to The Boeing Company Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes, certificated in any category, with an original standard airworthiness certificate or original export certificate of airworthiness issued on or before the effective date of this AD.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by significant changes made to the airworthiness limitations (AWLs) related to fuel tank ignition prevention. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Maintenance or Inspection Program Revision
Within 60 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate all information in Section A, including Subsections A.1 and A.2, of Boeing 727-100/200 Airworthiness Limitations (AWLs) D6-8766-AWL, dated December 2016. The initial compliance times for the airworthiness limitation instruction (ALI) items are within the applicable compliance times specified in paragraphs (g)(1) through (g)(6) of this AD.
(1) For AWL No. 28-AWL-01, ``External Wires Over Center Fuel Tank (Tank No. 2)'': at the applicable time specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) For airplanes that have been previously inspected as specified in 28-AWL-01 as of the effective date of this AD: Conduct the inspection within 120 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in 28-AWL-01 as of the effective date of this AD: Conduct the inspection within 12 months after the effective date of this AD.
(2) For AWL No. 28-AWL-16, ``Over-Current and Arcing Protection Electrical Design Features Operation--Boost Pump Ground Fault Interrupter (GFI)'': at the applicable time specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD.
(i) For airplanes that have been previously inspected as specified in 28-AWL-16 as of the effective date of this AD: Conduct the inspection within 12 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in 28-AWL-16 as of the effective date of this AD: Conduct the inspection within 90 days after the effective date of this AD.
(3) For AWL No. 28-AWL-17, ``Auxiliary Tank Fuel Boost Pump Power Failed On Protection System'': at the applicable time specified in paragraph (g)(3)(i) or (g)(3)(ii) of this AD.
(i) For airplanes that have been previously inspected as specified in 28-AWL-17 as of the effective date of this AD: Conduct the inspection within 12 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in 28-AWL-17 as of the effective date of this AD: Conduct the inspection within 90 days after the effective date of this AD.
(4) For AWL No. 28-AWL-18, ``Fuel Quantity Indicating System (FQIS)--Out-Tank Wiring Lightning Shield to Ground Termination and Joint Resistance for the Volumetric Top-Off (VTO) Unit (If Installed)'': at the applicable time specified in paragraph (g)(4)(i) or (g)(4)(ii) of this AD.
(i) For airplanes that have been previously inspected as specified in 28-AWL-18 as of the effective date of this AD: Conduct the inspection within 120 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in 28-AWL-18: Conduct the inspection within 12 months after the effective date of this AD.
(5) For AWL No. 28-AWL-22, ``AC Fuel Boost Pump Bonding Installation'': at the applicable time specified in paragraph (g)(5)(i) or (g)(5)(ii) of this AD.
(i) For airplanes that have been previously inspected as specified in 28-AWL-22 as of the effective date of this AD: Conduct the inspection within 72 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in 28-AWL-22 as of the effective date of this AD: Conduct the inspection within 12 months after the effective date of this AD.
(6) For AWL No. 28-AWL-24, ``Motor Operated Valve Bonding Jumper Installation--Fault Current Protection'': at the applicable time specified in paragraph (g)(6)(i) or (g)(6)(ii) of this AD.
(i) For airplanes that have been previously inspected as specified in 28-AWL-24 as of the effective date of this AD: Conduct the inspection within 60 months after the most recent inspection.
(ii) For airplanes that have not been inspected as specified in 28-AWL-24 as of the effective date of this AD: Conduct the inspection within 12 months after the effective date of this AD.
(h) Additional Acceptable Wire Types and Sleeving
(1) Where AWL No. 28-AWL-03 identifies wire types BMS 13-48, BMS 13-58, and BMS 13-60, the following acceptable wire types and cables can be added to AWL No. 28-AWL-03: MIL-W-22759/16, SAE AS22759/16 (Formerly M22759/16), MIL-W-22759/32, SAE AS22759/32 (Formerly M22759/32), MIL-W-22759/34, SAE AS22759/34 (Formerly M22759/34), MIL-W-22759/41, SAE AS22759/41 (Formerly M22759/41), MIL-W-22759/86, SAE AS22759/86 (Formerly M22759/86), MIL-W-22759/87, SAE AS22759/87 (Formerly M22759/87), MIL-W-22759/92 and SAE AS22759/92 (Formerly M22759/92); and MIL-C-27500 cables that are constructed from the MIL
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specification wire types identified above; and NEMA WC 27500 cables that are constructed from the SAE specification wire types identified above.
(2) Where AWL No. 28-AWL-03 identifies TFE-2X Standard wall for wire sleeving, the following acceptable sleeving materials can be added to AWL No. 28-AWL-03: Roundit 2000NX and Varglas Type HO, HP, or HM, Grade A.
(i) No Alternative Actions, Intervals, and Critical Design Configuration Control Limitations (CDCCLs)
After the maintenance or inspection program, as applicable, has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, and CDCCLs may be used unless the actions, intervals, and CDCCLs are approved as an alternative method of compliance (AMOC), in accordance with the procedures specified in paragraph (k) of this AD.
(j) Terminating Actions
Accomplishment of the revision required by paragraph (g) of this AD terminates the actions specified in paragraphs (j)(1) through (j)(5) of this AD for the airplane on which the revision has been incorporated.
(1) The revision required by paragraph (g) of AD 2008-04-10 R1.
(2) The revision required by paragraph (h) of AD 2009-05-03.
(3) The revision required by paragraph (j) of AD 2011-12-05.
(4) The revision required by paragraph (h) of AD 2013-22-03.
(5) The revision required by paragraphs (n)(1) and (n)(2) of AD 2013-24-15.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (l)(1) of this AD. Information may be emailed to: email protected.
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office.
(3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD.
(l) Related Information
(1) For more information about this AD, contact Christopher Baker, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW, Renton, WA 98057-3356; phone: 425-917-
6498; fax: 425-917-6590; email: email protected.
(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on January 26, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification Service.
FR Doc. 2018-02085 Filed 2-7-18; 8:45 am
BILLING CODE 4910-13-P
