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[Federal Register: April 14, 2008 (Volume 73, Number 72)] 

[Rules and Regulations] 

[Page 19975-19977] 

From the Federal Register Online via GPO Access [wais.access.gpo.gov] 

[DOCID:fr14ap08-8] 

–––––––––––––––––––––––––––––––––– 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-2008-0014; Directorate Identifier 2007-NM-249-AD; Amendment 39-15456; 

AD 2008-08-04] 

RIN 2120-AA64 

Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes 

AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). 

ACTION: Final rule. 

–––––––––––––––––––––––––––––––––– 

SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to 

certain Airbus Model A318, A319, A320, and A321 airplanes. That AD currently requires repetitive 

inspections for cracking in the forward lug of the support rib 5 fitting of both main landing gear 

(MLG), and repair if necessary. The existing AD also provides optional terminating actions for 

certain airplanes, as well as other optional methods for complying with the inspection requirements of 

the existing AD. This new AD continues to require repetitive inspections for cracking in the forward 

lug of the support rib 5 fitting of the left and right MLG at new repetitive intervals in accordance with 

new service information, and repair or replacement of any cracked MLG fitting if necessary. This 

new AD also requires modification of the rib bushings of the left and right MLG, which would end 

the repetitive inspections. This AD results from cracks found in the forward lug of the MLG support 

rib 5 fitting. We are issuing this AD to prevent cracking in the forward lug of the MLG, which could 

result in failure of the lug and consequent collapse of the MLG during takeoff or landing. 

DATES: This AD becomes effective May 19, 2008. 

 The Director of the Federal Register approved the incorporation by reference of certain 

publications listed in the AD as of May 19, 2008. 

ADDRESSES: For service information identified in this AD, contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 
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Examining the AD Docket 

 You may examine the AD docket on the Internet at http://www.regulations.gov; 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 AD, the regulatory evaluation, any comments received, and 

other information. The address for the Docket Office (telephone 800-647-5527) is the Document 

Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building 

Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, International 

Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057-3356; telephone (425) 227-2141; fax (425) 227-1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

 The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include 

an AD that supersedes AD 2006-11-04, amendment 39-14608 (71 FR 29578, May 23, 2006). The 

existing AD applies to certain Airbus Model A318, A319, A320, and A321 airplanes. That NPRM 

was published in the Federal Register on January 14, 2008 (73 FR 2200). That NPRM proposed to 

continue to require repetitive inspections for cracking in the forward lug of the support rib 5 fitting of 

the left and right main landing gear (MLG) at new repetitive intervals in accordance with new service 

information, and repair or replacement of any cracked MLG fitting if necessary. That NPRM also 

proposed to require modification of the rib bushings of the left and right MLG, which would end the 

repetitive inspections. 

Comments 

 We gave the public the opportunity to participate in developing this AD. We received no 

comments on the NPRM or on the determination of the cost to the public. 

Conclusion 

 We reviewed the relevant data and determined that air safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

 This AD affects about 466 airplanes of U.S. registry. 

 The actions that are required by AD 2006-11-04 and retained in this AD take about 2 work hours 

per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost 

of the currently required actions is $160 per airplane, per inspection cycle. 

 The new required inspections take between 3 and 4 work hours per airplane, depending on the 

type of inspection accomplished, at an average labor rate of $80 per work hour. Based on these 

figures, the estimated cost of the new inspections specified in this AD for U.S. operators is between 

$111,840 and $149,120, or between $240 and $320 per airplane, per inspection cycle. 

 The new required modification takes about 73 work hours per airplane, at an average labor rate 

of $80 per work hour. Required parts cost $3,850 per airplane. Based on these figures, the estimated 

cost of the new modification specified in this AD for U.S. operators is $4,515,540, or $9,690 per 

airplane. 
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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. 

Regulatory Findings 

 We have determined that this AD will not have federalism implications under Executive Order 

13132. This AD will 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 that this AD: 

 (1) Is not a ''significant regulatory action'' under Executive Order 12866; 

 (2) Is not a ''significant rule'' under 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 regulatory evaluation of the estimated costs to comply with this AD and placed it 

in the AD docket. 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, Incorporation by reference, Safety. 

Adoption of the Amendment 

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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. 

§ 39.13 [Amended] 

2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39-14608 

(71 FR 29578, May 23, 2006) and by adding the following new airworthiness directive (AD): 
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FAA 

Aircraft Certification Service

AIRWORTHINESS DIRECTIVE

www.faa.gov/aircraft/safety/alerts/ 

www.gpoaccess.gov/fr/advanced.html

2008-08-04 Airbus: Amendment 39-15456. Docket No. FAA-2008-0014; Directorate Identifier 

2007-NM-249-AD. 

Effective Date 

 (a) This AD becomes effective May 19, 2008. 

Affected ADs 

 (b) This AD supersedes AD 2006-11-04. 

Applicability 

 (c) This AD applies to Airbus Model A318, A319, A320, and A321 airplanes, certificated in any 

category, except airplanes on which Airbus Modification 32025 has been accomplished in 

production. 

Unsafe Condition 

 (d) This AD results from cracks found in the forward lug of the main landing gear (MLG) 

support rib 5 fitting. We are issuing this AD to prevent cracking in the forward lug of the MLG, 

which could result in failure of the lug and consequent collapse of the MLG during takeoff or 

landing. 

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. 

Restatement of Certain Requirements of AD 2006-11-04 

Repetitive Detailed Inspections 

 (f) Within 8 days after June 7, 2006 (the effective date of AD 2006-11-04), or before further 

flight after a hard landing, whichever is first: Perform a detailed inspection for cracking in the 

forward lug of the support rib 5 fitting of the left- and right-hand MLG, and, if any crack is found, 

replace the MLG fitting with a new fitting before further flight, in accordance with a method 

approved by either the Manager, International Branch, ANM-116, FAA; or the European Aviation 

Safety Agency (EASA) (or its delegated agent). Accomplishing the actions specified in the Airbus 

A318/A319/A320/A321 Nondestructive Testing Manual, Chapter 51-90-00, Revision dated February 

1, 2003, is one approved method for performing the detailed inspection. Repeat the inspection 

thereafter at intervals not to exceed 8 days, or before further flight after a hard landing, whichever is 

first. As of the effective date of this AD, the repetitive inspections required by paragraph (i) of this 

AD must be accomplished in lieu of the repetitive inspections required by this paragraph. 
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 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 mirror, magnifying lenses, etc., may be necessary. Surface cleaning and 

elaborate procedures may be required.'' 

Optional Inspection Method 

 (g) Performing an ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting 

of the left- and right-hand MLG in accordance with a method approved by the Manager, International 

Branch, ANM-116; or the EASA (or its delegated agent; is an acceptable alternative method of 

compliance for the initial and repetitive inspections required by paragraph (f) of this AD. Doing the 

actions specified in the Airbus A318/A319/A320/A321 Nondestructive Testing Manual, Chapter 57-

29-03, Revision dated February 1, 2005 (for Model A318, A319, and A320 airplanes), or Chapter 57-

29-04, Revision dated May 1, 2005 (for Model A321 airplanes), as applicable, is one approved 

method for performing the ultrasonic inspection. 

Optional Terminating Action 

 (h) For Model A319, A320, and A321 airplanes: Repair of the forward lugs of the support rib 5 

fitting of the left- and right-hand MLG in accordance with a method approved by the Manager, 

International Branch, ANM-116; or the EASA (or its delegated agent); constitutes terminating action 

for the requirements of this AD. Doing the repair in accordance with Airbus A319 Structural Repair 

Manual (SRM), Chapter 5.C., 57-26-13, Revision dated November 1, 2004; Airbus A320 SRM, 

Chapter 5.D., 57-26-13, Revision dated November 1, 2004; or Airbus A321 SRM, Chapter 5.D., 57-

26-13, Revision dated February 1, 2005; as applicable; is one approved method. 

New Requirements of This AD 

New Repetitive Inspections 

 (i) At the applicable time specified in Table 1 of this AD, or before further flight after a hard 

landing, whichever is first: Do a visual inspection or ultrasonic inspection for cracking in the forward 

lug of the support rib 5 fitting of the left and right MLG, in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320-57-1138, Revision 01, dated October 27, 2006. Repeat 

the inspection thereafter at the applicable interval specified in Table 1 of this AD or before further 

flight after a hard landing, whichever is first, until the modification required by paragraph (k) of this 

AD has been accomplished. Accomplishing the initial inspection terminates the requirements of 

paragraph (f) of this AD. 

Table 1 – Compliance Times 

Airplanes Initial Inspection Repetitive Interval 

If the most recent inspection is a detailed inspection 

done in accordance with paragraph (f) of this AD, 

inspect within 150 flight cycles after the most 

recent detailed inspection. 

Within 150 flight cycles 

after a visual inspection 

Model A318, 

A319, and 

A320 airplanes 

If the most recent inspection is an ultrasonic 

inspection done in accordance with paragraph (g) of 

this AD, inspect within 940 flight cycles after the 

most recent ultrasonic inspection. 

Within 940 flight cycles 

after an ultrasonic 

inspection 
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If the most recent inspection is a detailed inspection 

done in accordance with paragraph (f) of this AD, 

inspect within 100 flight cycles after the most 

recent detailed inspection. 

Within 100 flight cycles 

after a visual inspection 

Model A321 

airplanes 

If the most recent inspection is an ultrasonic 

inspection done in accordance with paragraph (g) of 

this AD, inspect within 630 flight cycles after the 

most recent ultrasonic inspection. 

Within 630 flight cycles 

after an ultrasonic 

inspection 

Corrective Action 

 (j) If any cracking is found during any inspection required by paragraph (i) of this AD: Before 

further flight, repair or replace the cracked MLG fitting using a method approved by either the 

Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or the EASA (or its 

delegated agent). 

Terminating Action 

 (k) Within 60 months after the effective date of this AD, modify the rib bushings of the left and 

right MLG, by accomplishing all of the applicable actions specified in the Accomplishment 

Instructions of Airbus Service Bulletin A320-57-1118, Revision 03, dated April 23, 2007. 

Accomplishing the modification terminates the requirements of this AD. 

Credit for Actions Done According to Previous Issue of Service Bulletin 

 (l) For Model A319, A320, and A321 airplanes, modifying the lugs of the support rib 5 fitting of 

the left and right MLG is acceptable for compliance with the requirements of paragraph (k) of this 

AD if done before the effective date of this AD in accordance with one of the following service 

bulletins: Airbus Service Bulletin A320-57-1118, dated September 5, 2002; Revision 01, dated 

August 28, 2003; or Revision 02, dated August 2, 2006. 

Alternative Methods of Compliance (AMOCs) 

 (m)(1) The Manager, International Branch, ANM-116, FAA, has the authority to approve 

AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. 

 (2) To request a different method of compliance or a different compliance time for this AD, 

follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards 

District Office (FSDO), or lacking a PI, your local FSDO. 

 (3) AMOCs approved previously in accordance with AD 2006-11-04 are approved as AMOCs 

for the corresponding provisions of this AD. 

Related Information 

 (n) EASA airworthiness directive 2007-0213, dated August 7, 2007, also addresses the subject of 

this AD. 
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Material Incorporated by Reference

 (o) You must use Airbus Service Bulletin A320-57-1118, Revision 03, dated April 23, 2007; and 

Airbus Service Bulletin A320-57-1138, Revision 01, dated October 27, 2006; as applicable; to 

perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of 

the Federal Register approved the incorporation by reference of these documents in accordance with 

5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, for a copy of this service information. You may review copies at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and 

Records Administration (NARA). For information on the availability of this material at NARA, call 

202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. 

 Issued in Renton, Washington, on March 31, 2008. 

Dionne Palermo, 

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. 

[FR Doc. E8-7182 Filed 4-11-08; 8:45 am]