Federal Register / Vol. 73, No. 72 / Monday, April 14, 2008 / Rules and Regulations 19975 

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. 

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. 

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. 


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19976 Federal Register / Vol. 73, No. 72 / Monday, April 14, 2008 / Rules and Regulations 

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): 

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. 

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 righthand 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 

Model A318, A319, and 

A320 airplanes.

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. 

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. 

Model A321 airplanes ... 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. 

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. 


cprice-sewell on PROD1PC62 with RULES
Federal Register / Vol. 73, No. 72 / Monday, April 14, 2008 / Rules and Regulations 19977 

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. 

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] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0420; Directorate 

Identifier 2008–NE–10–AD; Amendment 39–

15466; AD 2008–08–14] 

RIN 2120–AA64 

Airworthiness Directives; Lycoming 

Engines IO, (L)IO, TIO, (L)TIO, AEIO, 

AIO, IGO, IVO, and HIO Series 

Reciprocating Engines, Teledyne 

Continental Motors (TCM) TSIO–360–

RB Reciprocating Engines, and 

Superior Air Parts, Inc. IO–360 Series 

Reciprocating Engines With Certain 

Precision Airmotive LLC RSA–5 and 

RSA–10 Series Fuel Injection Servos 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: This document publishes in 

the Federal Register an amendment 

adopting emergency airworthiness 

directive (AD) 2008–06–51 that was sent 

previously to all known U.S. owners 

and operators of Lycoming Engines IO, 

(L)IO, TIO, (L)TIO, AEIO, AIO, IGO, 

IVO, and HIO series reciprocating 

engines, TCM TSIO–360–RB 

reciprocating engines, and Superior Air 

Parts, Inc. IO–360 series reciprocating 

engines with certain Precision 

Airmotive LLC RSA–5 and RSA–10 

series fuel injection servos. This AD 

results from eighteen reports of fuel 

injection servo plugs, part number (P/N) 

383493, that had loosened or completely 

backed out of the threaded plug hole on 

the regulator cover of the fuel injection 

servo. These servo plugs were installed 

with servo plug gasket, P/N 365533, 

under the plug hex-head. We are issuing 

this AD to prevent a lean running 

engine, which could result in a 

substantial loss of engine power and 

subsequent loss of control of the 

airplane. 

DATES: This AD becomes effective April 

29, 2008 to all persons except those 

persons to whom it was made 

immediately effective by emergency AD 

2008–06–51, issued on March 12, 2008, 

which contained the requirements of 

this amendment. 

We must receive any comments on 

this AD by June 13, 2008. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

Contact Precision Airmotive LLC at 

http://www.precisionairmotive.com for 

the service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: For 

Precision Airmotive LLC, Richard 

Simonson, Aerospace Engineer, 

Propulsion Branch, FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington 

98055; e-mail: 

Richard.simonson@faa.gov; telephone: 

(425) 917–6507; fax: (425) 917–6590. 

For Lycoming Engines, Norm 

Perenson, Aerospace Engineer, New 

York Aircraft Certification Office, FAA, 

Engine & Propeller Directorate, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; e-mail: 

Norman.perenson@faa.gov; telephone: 

(516) 228–7337; fax: (516) 794–5531. 

For Teledyne Continental Motors, 

Kevin Brane, Aerospace Engineer, 

Atlanta Aircraft Certification Office, 

FAA, Small Airplane Directorate, One 

Crown Center, 1895 Phoenix Blvd., 

Suite 450, Atlanta, GA 30349; e-mail: 

kevin.brane@faa.gov; telephone: (770) 

703–6063; fax: (770) 703–6097. 

For Superior Air Parts, Inc., Tausif 

Butt, Aerospace Engineer, Special 

Certification Office, FAA, Rotorcraft 

Directorate, Southwest Regional 

Headquarters, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; e-mail: 

Tausif.butt@faa.gov; telephone: (817) 

222–5195; fax: (817) 222–5785. 

SUPPLEMENTARY INFORMATION: On March 

12, 2008, the FAA issued emergency AD 

2008–06–51, that applies to Lycoming 

Engines IO, (L)IO, TIO, (L)TIO, AEIO, 


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