Airworthiness directives: Ostmecklenburgische Flugzeugbau GmbH,
[Federal Register: August 18, 2004 (Volume 69, Number 159)]
[Proposed Rules]
[Page 51206-51208]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18au04-20]
[[Page 51206]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. 2003-CE-67-AD]
RIN 2120-AA64
Airworthiness Directives; Ostmecklenburgische Flugzeugbau GmbH Model OMF-100-160 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Ostmecklenburgische Flugzeugbau GmbH (OMF) Model OMF-100- 160 airplanes. This proposed AD would require you to inspect the outside tube (cage) that supports the main landing gear leg for cracks, repair if cracks are found, and inspect the thickness of the tube if no cracks were found and reinforce the tube as necessary. This proposed AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this proposed AD to detect, correct, and prevent future cracks in the outside tube of the main landing gear leg, which could result in structural failure of the fuselage tubing assembly. This failure could lead to loss of control of the airplane.
DATES: We must receive any comments on this proposed AD by September 22, 2004.
ADDRESSES: Use one of the following to submit comments on this proposed AD:
By mail: FAA, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 2003-CE-67-AD, 901 Locust, Room 506, Kansas City, Missouri 64106.
By fax: (816) 329-3771.
By e-mail: 9-ACE-7-Docket@faa.gov. Comments sent electronically must contain ``Docket No. 2003-CE-67-AD `` in the subject line. If you send comments electronically as attached electronic files, the files must be formatted in Microsoft Word 97 for Windows or ASCII.
You may get the service information identified in this proposed AD from Ostmecklenburgische Flugzeugbau GmbH, Flughafenstra[azlig]e, 17039 Trollenhagen, Federal Republic of Germany.
You may view the AD docket at FAA, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 2003-CE-67-AD, 901 Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. to 4 p.m., Monday through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, ACE-112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri, 64106; telephone: 816-329-4146; facsimile: 816-329-4149.
SUPPLEMENTARY INFORMATION:
Comments Invited
How do I comment on this proposed AD? We invite you to submit any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ``AD Docket No. 2003-CE-67-AD'' in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self- addressed, stamped postcard with the docket number written on it. We will date-stamp your postcard and mail it back to you.
Are there any specific portions of this proposed AD I should pay attention to? We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. If you contact us through a nonwritten communication and that contact relates to a substantive part of this proposed AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend this proposed AD in light of those comments and contacts.
Discussion
What events have caused this proposed AD? The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority for Germany, recently notified the FAA that an unsafe condition may exist on certain OMF Model OMF-100-160 airplanes. The LBA reports that the manufacturer received a report of cracks in the outside fuselage tube that supports the main landing gear leg. Further investigation revealed that one manufacturer of fuselage tubes used out-of-design dimensions for the tube elements.
What are the consequences if the condition is not corrected? Cracks in the outside tube of the main landing gear leg, if not detected, corrected, and prevented, could result in structural failure of the fuselage tubing assembly. This failure could lead to loss of control of the airplane.
Is there service information that applies to this subject? OMF has issued Alert Service Bulletin No. 1107/0002, dated September 16, 2003.
What are the provisions of this service information? The service bulletin includes procedures for:
--Inspecting the tubing that supports the main landing gear leg; --Inspecting the tube thickness and reinforcing the tube as necessary; and --Obtaining repair instructions if cracks are found.
What action did the LBA take? The LBA classified this service bulletin as mandatory and issued German AD Number 2003-272, dated October 17, 2003, to ensure the continued airworthiness of these airplanes in Germany.
Did the LBA inform the United States under the bilateral airworthiness agreement? These OMF Model OMF-100-160 airplanes are manufactured in Germany and are type-certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement.
Under this bilateral airworthiness agreement, the LBA has kept us informed of the situation described above.
FAA's Determination and Requirements of This Proposed AD
What has FAA decided? We have examined the LBA's findings, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.
Since the unsafe condition described previously is likely to exist or develop on other OMF airplanes of the same type design that are registered in the United States, we are proposing AD action to detect, correct, and prevent future cracks in the outside tube of the main landing gear leg. These cracks could result in structural failure of the fuselage tubing assembly and lead to loss of control of the airplane.
What would this proposed AD require? This proposed AD would require you to incorporate the actions in the previously-referenced service bulletin.
How does the revision to 14 CFR part 39 affect this proposed AD? On July 10, 2002, we published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs FAA's AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions.
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Costs of Compliance
How many airplanes would this proposed AD impact? We estimate that this proposed AD affects 11 airplanes on the U.S. registry.
What would be the cost impact of this proposed AD on owners/ operators of the affected airplanes? We estimate the following costs to accomplish these proposed inspections:
Total cost Total cost Labor cost
Parts cost
per
on U.S. airplane operators
Inspection for cracks--2
N/A
$130
$1,430 workhours est. $65 per hour = $130......................... Inspection for inadequate
N/A
130
(1) thickness of tubing that supports the main landing gear leg--2 workhours est. $65 the per hour = $130......
\1\ OMF will cover the cost for special inspection.
We estimate the following costs to accomplish any necessary repairs that would be required based on the results of these proposed inspections. We have no way of determining the number of airplanes that may need this repair:
Total cost Labor cost
Parts cost
per airplane
85 workhours X $65 per hour = None per
$5,525 $5,525.
manufacturer.
Regulatory Findings
Would this proposed AD impact various entities? 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 responsibilities among the various levels of government.
Would this proposed AD involve a significant rule or regulatory action? For the reasons discussed above, I certify that this proposed AD:
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); and
3. 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 summary of the costs to comply with this proposed AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ``AD Docket No. 2003-CE-67-AD'' in your request.
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 Federal Aviation Administration proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD):
Ostmecklenburgische Flugzeugbau GmbH: Docket No. 2003-CE-67-AD
When Is the Last Date I Can Submit Comments on This Proposed AD?
(a) We must receive comments on this proposed airworthiness directive (AD) by September 22, 2004.
What Other ADs Are Affected by This Action?
(b) None.
What Airplanes Are Affected by This AD?
(c) This AD affects Model OMF-100-160 airplanes, serial numbers 0006, 0007, 0012 through 0015, 0017, 0018, 0020, 0021, 0024, 0025, 0028, and 0029; that are certificated in any category.
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of cracks in the fuselage tubing assembly and inadequate thickness of tubing that supports the main landing gear leg. The actions specified in this AD are intended to detect, correct, and prevent future cracks in the tubing for the main landing gear leg, which could result in failure of the fuselage tubing assembly. This failure could lead to loss of control of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
Actions
Compliance
Procedures
(1) Inspect the main landing Inspect the
Inspect following gear leg support for cracks airplane within the procedures in 50 hours time-in- OMF Alert Service service (TIS) Bulletin No. 1107/ after the
0002, dated effective date of September 16, this AD.
2003. (2) If cracks are found during Repair prior to Contact an any inspection required in
further flight Ostmecklengurgisc paragraph (e)(1) or (e)(3)(ii) after the
he Flugzeugbau of this AD, obtain repair
inspection where GmbH (OMF) instructions from the
cracks are found. representative at manufacturer through the FAA
1-819-377-1177 and incorporate the repair
for repair instructions. This repair
instructions and eliminates the repetitive
incorporate these inspection requirement of this
instructions. AD
Summarize and copy all correspondence and send to FAA at the address specified in paragraph (f) of this AD.
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(3) If no cracks are found
Inspect for tubing Inspect following during the inspection required thickness of the procedures in OMF in paragraph (e)(1) of this AD, airplane within Alert Service do the following:
50 hours TIS
Bulletin No. 1107/ after the initial 0002, dated inspection
September 16, required in
2003. Reinforce paragraph (e)(1) with instructions of this AD.
from the Reinforce prior manufacturer. to further flight Contact an after the
Ostmecklengurgisc inspection
he Flugzeugbau required in
GmbH (OMF) paragraph
representative at (e)(3)(i)of this 1-819-377-1177 AD. Repetitively for repair inspect main
instructions and landing gear leg incorporate these support within 50 instructions. hours TIS after Summarize and the initial
copy all inspection
correspondence required by
and send to FAA paragraph (e)(1) at the address of this AD and specified in thereafter at paragraph (f) of intervals not to this AD. exceed 50 hours TIS.
(i) inspect tubing for proper thickness and make any appropriate reinforcements
(ii) repetitively inspect main landing gear leg support for cracks
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Karl Schletzbaum, Aerospace Engineer, ACE-112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri, 64106; telephone: 816-329-4146; facsimile: 816-329-4149.
May I Get Copies of the Documents Referenced in This AD?
(g) You may get copies of the documents referenced in this AD from Ostmecklenburgische Flugzeugbau GmbH, Flughafenstra[szlig]e, 17039 Trollenhagen, Federal Republic of Germany. You may view these documents at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.
Is There Other Information That Relates to This Subject?
(h) LBA Airworthiness Directive No. 2003-272, dated October 7, 2003, and OMF Alert Service Bulletin 1107/0002, dated September 16, 2003, pertain to the subject of this AD.
Issued in Kansas City, Missouri, on August 11, 2004. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-18927 Filed 8-17-04; 8:45 am]
BILLING CODE 4910-13-P
