Source: https://www.federalregister.gov/documents/2015/07/14/2015-17201/airworthiness-directives-airbus-airplanes
Timestamp: 2018-04-23 02:04:01
Document Index: 283775575

Matched Legal Cases: ['art 4', 'art 4', 'art 4', 'art 4', 'art 4', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', '§\u200939', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1', 'art 1']

We must receive comments on this proposed AD by August 28, 2015.
80 FR 40942
40942-40947 (6 pages)
Docket No. FAA-2015-2461
Directorate Identifier 2013-NM-202-AD
FAA-2015-2461
2013-NM-202-AD Airbus Model A300, A310, and A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4?605R Variant F airplanes (collectively called Model A300-600 series airplanes)
(g) Retained Revision of Airworthiness Limitation Section (ALS)
(h) Retained Initial Compliance Times and Repetitive Inspections
(i) Retained Special Compliance Times
https://www.federalregister.gov/d/2015-17201 https://www.federalregister.gov/d/2015-17201
We propose to supersede Airworthiness Directive (AD) 2009-18-15 for all Airbus Model A300, A310, and A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 2009-18-15 currently requires revising the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness (ICA) to require additional life limits and/or replacements for certain main landing gear and nose landing gear components. Since we issued AD 2009-18-15, we have determined that existing maintenance requirements and airworthiness limitations are inadequate to ensure the structural integrity of the airplane. This proposed AD would require revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. We are proposing this AD to prevent failure of certain system components, which could result in reduced structural integrity of the airplane.
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-2461; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.
We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include “Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-202-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.
On August 24, 2009, we issued AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). AD 2009-18-15 requires actions intended to address an unsafe condition for all Airbus Model A300, A310, and A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes).
Since we issued AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009), we have determined that more restrictive maintenance requirements and airworthiness limitations are necessary.
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013-0248, dated October 14, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or “the MCAI”), to correct an unsafe condition for all Model A300, A310, and A300-600 series airplanes. The MCAI states:
The mandatory instructions and airworthiness limitations applicable to the Aging Systems Maintenance (ASM) are specified in Airbus A310 or A300-600 ALS Part 4 documents, which are approved by the European Aviation Safety Agency (EASA). EASA AD 2007-0092 [http://ad.easa.europa.eu/​blob/​easa_​ad_​2007_​0092.pdf/​AD_​2007-0092] [which corresponds to FAA AD 2009-06-06, Amendment 39-15842 (74 FR 12228, March 24, 2009)] was issued to require compliance to the requirements as specified in these documents.
The revision 02 of Airbus A310 and Airbus A300-600 ALS Part 4 documents introduces more restrictive maintenance requirements and/or airworthiness limitations. Failure to comply with the instructions of ALS Part 4 could result in an unsafe condition [reduced structural integrity of the airplane.]
For the reasons described above, this new [EASA] AD retains the requirements of EASA AD 2007-0092, which is superseded, and requires the implementation of the new or more restrictive maintenance requirements and/or airworthiness limitations as specified in Airbus A310 ALS Part 4, Revision 02, or Airbus A300-600 ALS Part 4, Revision 02, as applicable to aeroplane type/model.
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-2461.Start Printed Page 40943
Airbus has issued the following service information, which describes procedures for revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations.
For Model A300 series airplanes: “Sub-part 1-2: Life Limits,” and “Sub-part 1-3: Demonstrated fatigue lives” of Part 1, “Safe Life Airworthiness Limitation Items,” Revision 01, dated September 5, 2013, of the Airbus Model A300 Airworthiness Limitations Section.
For Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes): “Sub-part 1-2: Life Limits,” and “Sub-part 1-3: Demonstrated fatigue lives” of Part 1, “Safe Life Airworthiness Limitation Items,” Revision 01, dated September 5, 2013, of the Airbus Model A300-600 Airworthiness Limitations Section.
For Model A310 series airplanes: “Sub-part 1-2: Life Limits,” and “Sub-part 1-3: Demonstrated fatigue lives” of Part 1, “Safe Life Airworthiness Limitation Items,” Revision 01, dated September 5, 2013, of the Airbus Model A310 Airworthiness Limitations Section.
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 of this NPRM.
The ALS revision required by AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009), takes about 1 work-hour per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2009-18-15 is $85 per product.
We also estimate that it would take about 1 work-hour per product to comply with the new ALS revision of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $15,045, or $85 per product.
2. The FAA amends § 39.13 by removing Airworthiness Directive AD 2009-18-15, Amendment 39-16011 ( 74 FR 48143, September 22, 2009), and adding the following new AD:
Airbus: Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-202-AD.
We must receive comments by August 28, 2015.
This AD replaces AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009).
Air Transport Association (ATA) of America 32, Landing Gear.
This AD was prompted by a determination that existing maintenance requirements and airworthiness limitations are inadequate to ensure the structural integrity of the airplane. We are issuing this AD to prevent failure of certain system components, which could result in reduced structural integrity of the airplane.
This paragraph restates the requirements of paragraph (h) of AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). For Model A300, A310, and A300-600 series airplanes: Within 3 months after October 27, 2009 (the effective date of AD 2009-18-15), revise the ALS of the instructions for continued airworthiness (ICA) to incorporate the applicable document Start Printed Page 40944listed in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Accomplishing the actions specified in the applicable document satisfies the requirements of paragraph A. of AD 84-02-04, Amendment 39-4795.
(1) For Model A300 series airplanes: Incorporate the applicable document listed in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
(i) Section 05-10-00, Revision 28, dated February 27, 1998, of Chapter 05, “Service Life Limits and Maintenance Checks,” of the Airbus A300 Aircraft Maintenance Manual, except that the parts listed in table 1 to paragraph (g) of this AD are subject to the life limits defined in the document listed in paragraph (g)(1)(ii) of this AD.
Table 1 to Paragraph (g) of This AD—Parts Subject to the Life Limits Specified in the Document Identified in Paragraph (g)(1)(ii) of This AD
(3) For Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes): Incorporate “Sub-part 1-2: Life Limits,” and “Sub-part 1-3: Demonstrated Fatigue Lives” of Part 1, “Safe Life Airworthiness Limitation Items,” dated December 21, 2006, of the Airbus A300-600 ALS.
This paragraph restates the requirements of paragraph (i) of AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). Do the replacement at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, except as provided by paragraph (i) of this AD. The replacement must be done thereafter within the interval specified in the applicable document identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(1) For any life limitation/task that has been complied with before October 27, 2009 (the effective date of AD 2009-18-15, Amendment 39-16011), in accordance with the applicable document listed in paragraph (g)(1), (g)(2), or (g)(3) of this AD, or in accordance with paragraph (g) of AD 2009-18-15, use the last accomplishment of each limitation/task as a starting point for accomplishing each corresponding limitation/task required by this AD.
(2) For any life limitation/task that has not been complied with before October 27, 2009 (the effective date of AD 2009-18-15, Amendment 39-16011), in accordance with the applicable document listed in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, or in accordance with paragraph (g) of AD 2009-18-15, the initial compliance time starts from the date of initial entry into service as defined in the applicable document.
This paragraph restates the requirements of paragraph (j) of AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). For any airplane on which the history of accumulated landings is partial or unknown, or where the history of application details (airplane type, model, weight variant, etc.) is partial or unknown, with or without using the information in Airbus Service Information Letter 32-118, Revision 02, dated October 24, 2007: Parts listed in figure 1 to paragraph (i) of this AD must be replaced at the associated compliance time. The replacement must be done thereafter at the interval specified in the applicable document(s) specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.
Note 1 to paragraph (i) of this AD: Airbus Service Information Letter 32-118, Revision 02, dated October 24, 2007, provides operators with guidance on the means to assign a conservative calculated life to parts whose history of accumulated landings is partial or unknown; and to select the limitations applicable to parts whose history of application details (aircraft type, aircraft model, weight variant, etc.) is partial or unknown.
Figure 1 to Paragraph (i) of This AD—Special Compliance Times
Aircraft type applicability
Compliance time (whichever occurs first after the “start date”)
A32140032200xx X December 13, 2007 13,500 9 years.
A32140056200xx X December 13, 2007 13,500 9 years.
A32140056202xx X December 13, 2007 13,500 9 years.
Aft pintle pin A32140057200xx X December 13, 2007 13,500 9 years.
A32140057202xx X X December 13, 2007 13,500 9 years.
A32140062000xx X December 13, 2007 13,500 9 years.
A32140063000xx X X December 13, 2007 13,500 9 years.
A32140036200xx X December 13, 2007 13,500 9 years.
A32140036202xx X December 13, 2007 13,500 9 years.
A32140036204xx X December 13, 2007 13,500 9 years.
A32140036206xx X December 13, 2007 13,500 9 years.
Half ball housing (Fwd pintle bearing) A32140042200xx X X December 13, 2007 13,500 9 years.
A32140042202xx X X December 13, 2007 13,500 9 years.
A32140068002xx X December 13, 2007 13,500 9 years.
A32140068004xx X December 13, 2007 13,500 9 years.
A32140069002xx X X December 13, 2007 13,500 9 years.
A32140069004xx X X December 13, 2007 13,500 9 years.
Ball (Fwd pintle pin) A32140012202xx X December 13, 2007 13,500 9 years.
A32140043202xx X X December 13, 2007 13,500 9 years.
Pin (Multiple link/Frame 50) A53833451200xx X December 13, 2007 13,500 9 years..
A53833451206xx X December 13, 2007 13,500 9 years.
A53834451200xx X December 13, 2007 13,500 9 years.
A53834451202xx X X April 25, 2007 13,500 9 years.
Pin (Drop link/Frame 50) A53811122200xx X April 25, 2007 18,000 9 years.
MLG Barrel Assembly
Upper torque link pin nut 00-200-402 X December 13, 2007 N/A 30 months.
SL40089 X December 13, 2007 N/A 30 months.
SL40089P X December 13, 2007 N/A 30 months.
SL40123 X December 13, 2007 N/A 30 months.
SL40123P X X X April 25, 2007 N/A 30 months.
Torque link medium pin nut 00-200-358 X December 13, 2007 N/A 30 months.
SL40114P X X April 25, 2007 N/A 30 months.
SL40132 X December 13, 2007 N/A 30 months.
SL40132P X X April 25, 2007 N/A 30 months.
Attaching fitting pin C62311-1 X December 13, 2007 13,500 9 years.
C62311-20 X X April 25, 2007 13,500 9 years.
Pin (Connecting rod/Upper rod) C65815 X December 13, 2007 13,500 9 years.
C65815-1 X December 13, 2007 13,500 9 years.
C65815-20 X December 13, 2007 13,500 9 years.
C66472 X December 13, 2007 13,500 9 years.
C66472-1 X December 13, 2007 13,500 9 years.
C66472-20 X X April 25, 2007 13,500 9 years.
D52751 X April 25, 2007 18,000 9 years.
MLG Shock Absorber Assembly
Lower torque link pin nut 00-200-402 X December 13, 2007 N/A 30 months.
Bogie beam pivot pin nut SL40054 X December 13, 2007 at next removal/installation.1 2
SL40054P X X April 25, 2007 at next removal/installation.1 2
SL40413P X April 25, 2007 at next removal/installation.1 2
MLG Lock Link Assembly
Lock link medium pin C61485-1 X December 13, 2007 N/A 30 months.
C61485-20 X X April 25, 2007 N/A 30 months.
Pintle pin A32210079200xx X X X April 25, 2007 13,500 9 years.
NLG Telescopic Strut Assembly
Nut (Cylinder/Locking cylinder) C61375 X X April 25, 2007 13,500 9 years.
D55955 X X X April 25, 2007 13,500 9 years.
Locking sleeve C61389 X X December 13, 2007 13,200 9 years.
C61389-1 X X X April 25, 2007 13,500 9 years.
NLG Barrel Assembly
Pin (Clevis/Telescopic strut) C62231-1 X December 13, 2007 13,200 9 years.
C62231-2 X December 13, 2007 13,200 9 years.
C62231-20 X X X April 25, 2007 13,500 9 years.
D56530 X X X April 25, 2007 13,500 9 years.
Lower pin (Link/Clevis) C62268-1 X December 13, 2007 13,200 9 years.
C62268-2 X December 13, 2007 13,200 9 years.
C62268-20 X X X April 25, 2007 13,500 9 years.
Link (Clevis/Barrel) C62230-1 X X X April 25, 2007 13,500 9 years.
D56526 X X X April 25, 2007 13,500 9 years.
Upper pin (Link/Barrel) C62267-1 X December 13, 2007 13,200 9 years.
C62267-2 X December 13, 2007 13,200 9 years.
C62267-20 X X X April 25, 2007 13,500 9 years.
End fitting pin nut D68062 X X X December 13, 2007 at next removal/installation.2
MS17825-6 X X X December 13, 2007 at next removal/installation.2
End fitting pin AN6-17 X X X December 13, 2007 at next removal/installation.2
D61183 X X X December 13, 2007 at next removal/installation.2
D68063 X X X December 13, 2007 at next removal/installation.2
NAS1306-22D X X X December 13, 2007 at next removal/installation.2
End fitting C62032 X X X April 25, 2007 13,500 9 years.
C62032-1 X X X April 25, 2007 13,500 9 years.
Rack C61453 X December 13, 2007 13,200 9 years.
C61453-1 X X X April 25, 2007 13,500 9 years.
C61453-20 X X X April 25, 2007 13,500 9 years.
C61453-40 X X X April 25, 2007 13,500 9 years.
C61453-41 X X X April 25, 2007 13,500 9 years.
Torque link pin (Upper & Lower) C62223-1 X December 13, 2007 13,200 9 years.
C62223-20 X X X April 25, 2007 13,500 9 years.
Torque link medium pin nut SL40110P X X X April 25, 2007 N/A 30 months.
NLG Shock Absorber Assembly
Wheel axle nut C62879 X X X April 25, 2007 4,000 24 months.
Upper cam dowel C62270 X X X December 13, 2007 at next removal/installation.
Upper cam C62034-1 X X X April 25, 2007 13,500 9 years.
Lower cam C62035 X X X April 25, 2007 13,500 9 years.
Restrictor C62036 X December 13, 2007 13,200 9 years.
C62036-1 X December 13, 2007 13,200 9 years.
C62036-2 X December 13, 2007 13,200 9 years.
C67863 X December 13, 2007 13,200 9 years.
C67863-1 X X X April 25, 2007 13,500 9 years.
C67863-2 X X X April 25, 2007 13,500 9 years.
C67863-3 X December 13, 2007 13,500 9 years.
C67863-4 X X X April 25, 2007 13,500 9 years.
Lower cam dowel C62866 X X X December 13, 2007 at next removal/installation.2
Nut (S/A/Barrel) C64040 X December 13, 2007 at next removal/installation.1 2
C64040-1 X X X December 13, 2007 at next removal/installation.1 2
1 When the nut is temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no replacement is required provided the nut's removal and reinstallation are performed on the same assembly and neither the assembly nor the nut accumulates time in service during the period between the removal and reinstallation.
2 If the removal/installation was done after the start date, but before the effective date of this AD, the compliance time is within 3 months. after October 27, 2009 (the effective date of AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009)).
Within 3 months after the effective date of this AD: Revise the maintenance or inspection program, as applicable, to incorporate the applicable limitation, replacement, or inspection specified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable. Doing any task required by this paragraph terminates the corresponding task required by paragraph (g), (h), and (i) of this AD.
(1) For Model A300 series airplanes: Incorporate “Sub-part 1-2: Life Limits,” and “Sub-part 1-3: Demonstrated Fatigue Lives” of Part 1, “Safe Life Airworthiness Limitation Items,” Revision 01, dated September 5, 2013, of the Airbus A300 ALS.
(2) For Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4 605R Variant F airplanes (collectively Start Printed Page 40947called Model A300-600 series airplanes): Incorporate “Sub-part 1-2: Life Limits,” and “Sub-part 1-3: Demonstrated Fatigue Lives” of Part 1, “Safe Life Airworthiness Limitation Items,” Revision 01, dated September 5, 2013, of the Airbus A300-600 ALS.
(3) For Model A310 series airplanes: Incorporate “Sub-part 1-2: Life Limits,” and “Sub-part 1-3: Demonstrated Fatigue Lives” of Part 1, “Safe Life Airworthiness Limitation Items,” dated Revision 01, September 5, 2013, of the Airbus A310 ALS.
After accomplishment of the revision required by paragraph (j) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (l) of this AD.
(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013-0248, dated October 14, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-2461.
[FR Doc. 2015-17201 Filed 7-13-15; 8:45 am]