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[Federal Register: September 6, 2007 (Volume 72, Number 172)] 

[Rules and Regulations] 

[Page 51164-51167] 

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

[DOCID:fr06se07-3] 

–––––––––––––––––––––––––––––––––– 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-2007-27776; Directorate Identifier 2006-NM-170-AD; Amendment 39-15189; 

AD 2007-18-09] 

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 all 

Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 series airplanes, and 

Model A320-111 airplanes. That AD currently requires an inspection to determine whether certain 

braking and steering control units (BSCUs) are installed or have ever been installed. For airplanes on 

which certain BSCUs are installed or have ever been installed, the existing AD requires an inspection 

of the nose landing gear (NLG) upper support, and corrective action if necessary; and a check of the 

NLG strut inflation pressure, and an adjustment if necessary. For some of these airplanes, the existing 

AD also requires a revision to the aircraft flight manual to incorporate an operating procedure to 

recover normal steering in the event of a steering failure. This new AD instead requires repetitive 

inspections of the NLG upper support, and related investigative/corrective actions in accordance with 

new service information; and removes the one-time inspection that was required by the existing AD. 

This new AD also provides an optional terminating action for the repetitive inspections. This AD 

results from a report of an incident where an airplane landed with the NLG turned 90 degrees from 

centerline, and from additional reports of NLG upper support anti-rotation lugs rupturing in service. 

We are issuing this AD to prevent landings with the NLG turned 90 degrees from centerline, which 

could result in reduced controllability of the airplane. 

DATES: This AD becomes effective October 11, 2007. 

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

publication listed in the AD as of October 11, 2007. 

 On November 30, 2005 (70 FR 70715, November 23, 2005), the Director of the Federal Register 

approved the incorporation by reference of a certain publication listed in the AD. 
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ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at 

the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, 

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

 Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service 

information identified in this AD. 

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

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

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

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

 You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov 

or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket Operations office (telephone (800) 647-5527) is located on the 

ground floor of the West Building at the DOT street address stated in the ADDRESSES section. 

Discussion 

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

an AD that supersedes AD 2005-24-06, amendment 39-14386 (70 FR 70715, November 23, 2005). 

The existing AD applies to all Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-

200 series airplanes, and Model A320-111 airplanes. That NPRM was published in the Federal 

Register on April 5, 2007 (72 FR 16749). That NPRM proposed to continue to require an inspection 

to determine whether certain braking and steering control units (BSCUs) are installed or have ever 

been installed. For airplanes on which certain BSCUs are installed or have ever been installed, that 

NPRM proposed to continue to require a revision to the aircraft flight manual (AFM) to incorporate 

an operating procedure to recover normal steering in the event of a steering failure. That NPRM also 

proposed to require repetitive inspections of the nose landing gear (NLG) upper support, and related 

investigative/corrective actions, and an optional terminating action for the repetitive inspections. 

Comments 

 We provided the public the opportunity to participate in the development of this AD. We have 

considered the comments that have been received on the NPRM. 

Support for the AD 

 The National Transportation Safety Board supports the adoption of the AD. 

Request To Revise ''Optional Terminating Action'' Reference 

 Airbus requests that we rephrase the heading of paragraph (l), ''Optional Terminating Action,'' of 

the NPRM. Airbus states that the terminating action for the issue addressed by the NPRM is not yet 

available. According to Airbus, the terminating action will include implementation of a new BSCU 

standard, which is currently being defined. Therefore, Airbus suggests that instead of the title 

''Optional Terminating Action,'' we use a different title, such as ''Action that Renders Void the 

Requirements of this AD,'' or equivalent wording. Airbus states that it is correct to say that the 

actions proposed in paragraph (l) of the NPRM would render void the requirements of this AD, and 
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that no further action would be required by this AD. However, the terminating action for the issue 

will require installation of a new future BSCU standard. Airbus anticipates that it will require the 

installation of the future BSCU standard as a terminating action. 

 We disagree with the request to rephrase the title of paragraph (l) of this AD. We consider the 

phrase ''Action that Renders Void the Requirements of this AD,'' to be equivalent to the existing title 

''Optional Terminating Action.'' Furthermore, this AD is fully consistent with European Aviation 

Safety Agency (EASA) airworthiness directive 2006-0174, dated June 21, 2006, which is the parallel 

EASA airworthiness directive to this AD. If EASA supersedes airworthiness directive 2006-0174 for 

any reason, we will consider additional rulemaking. We have not changed the AD in this regard. 

Explanation of Editorial Change to Paragraph (l) 

 Paragraph (l) of the NPRM referred to ''standard L4.1 and L4.5.'' That paragraph should refer to 

''standard L4.1 or L4.5.'' We have revised paragraph (l) of the final rule accordingly. This change will 

not affect accomplishment of the optional terminating action. 

Clarification of Alternative Method of Compliance (AMOC) Paragraph 

 We have revised this action to clarify the appropriate procedure for notifying the principal 

inspector before using any approved AMOC on any airplane to which the AMOC applies. 

Conclusion 

 We have carefully reviewed the available data, including the comments received, and determined 

that air safety and the public interest require adopting the AD with the changes described previously. 

We have determined that these changes will neither increase the economic burden on any operator 

nor increase the scope of the AD. 

Costs of Compliance 

 This AD affects about 720 airplanes of U.S. registry. The following table provides the estimated 

costs for U.S. operators to comply with this AD. The average labor rate is $80 per work hour. 

Estimated Costs 

Action Work 

hours 

Parts Cost per 

airplane 

Fleet cost 

Records review (required by AD 2005-24-06) 1 None $80 $57,600 

AFM revision (required by AD 2005-24-06) 1 None $80 $57,600 

Special detailed inspection in accordance with 

new service information (new action) 

1 None $80, per 

inspection cycle 

$57,600, per 

inspection cycle 

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. 
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 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 39-14386 

(70 FR 70715, November 23, 2005) 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

2007-18-09 AIRBUS: Amendment 39-15189. Docket No. FAA-2007-27776; Directorate Identifier 

2006-NM-170-AD. 

Effective Date 

 (a) This AD becomes effective October 11, 2007. 

Affected ADs 

 (b) This AD supersedes AD 2005-24-06. 

Applicability 

 (c) This AD applies to all Airbus Model A318, A319, A320, and A321 airplanes. 

Unsafe Condition 

 (d) This AD results from a report of an incident where an airplane landed with the nose landing 

gear (NLG) turned 90 degrees from centerline, and from additional reports of NLG upper support 

anti-rotation lugs rupturing in service. We are issuing this AD to prevent landings with the NLG 

turned 90 degrees from centerline, which could result in reduced controllability of the airplane. 

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 2005-24-06 

Records Review 

 (f) Within 5 days after November 30, 2005 (the effective date of AD 2005-24-06), perform a 

records review to determine whether the airplane is equipped with or has ever been equipped with an 

enhanced manufacturing and maintainability (EMM) braking and steering control unit (BSCU) part 

number (P/N) E21327001 (standard L4.1, installed by Airbus Modification 26965, or Airbus Service 

Bulletin A320-32-1912) or P/N E21327003 (standard L4.5, installed by Airbus Modification 33376, 

or Airbus Service Bulletin A320-32-1261). Airbus Service Bulletin A320-32-1310, dated February 8, 

2006, is one approved method for doing the records review. 

 (g) For airplanes on which a records review required by paragraph (f) of this AD conclusively 

determines that the airplane is not and never has been equipped with a BSCU P/N E21327001 or P/N 

E21327003, no further action is required by this AD. 
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Airplane Flight Manual (AFM) Revision 

 (h) For airplanes that are not specified in paragraph (g) of this AD and on which Airbus 

Modification 31152 has not been incorporated in production (i.e., applicable only to aircraft with 

steering powered by the green hydraulic system): Within 10 days after November 30, 2005, revise the 

Limitation Section of the Airbus A318/319/320/321 Aircraft Flight Manual (AFM) to include the 

following information. This may be done by inserting a copy of this AD into the AFM: 

"The ECAM message, in case of a nose wheel steering failure, will be worded as follows: 

- "WHEEL N/W STRG FAULT" for aircraft with the FWC E3 and subsequent standards 

- "WHEEL N.W. STEER FAULT" for aircraft with the FWC E2 Standard. 

 If the L/G SHOCK ABSORBER FAULT ECAM caution is triggered at any time in flight, and 

the WHEEL N/W STRG FAULT ECAM caution is triggered after the landing gear extension: 

• When all landing gear doors are indicated closed on ECAM WHEEL page, reset the BSCU: 

 - A/SKID&N/W STRG---------------------------- OFF THEN ON 

• If the WHEEL N/W STRG FAULT ECAM caution is no longer displayed, this indicates a 

successful nose wheel re-centering and steering recovery. 

 - Rearm the AUTO BRAKE, if necessary. 

• If the WHEEL N/W STRG FAULT ECAM caution remains displayed, this indicates that the 

nose wheel steering remains lost, and that the nose wheels are not centered. 

- During landing, delay nose wheel touchdown for as long as possible. 

- Refer to the ECAM STATUS. 

 If the WHEEL N/W STRG FAULT ECAM caution appears, without the L/G SHOCK 

ABSORBER FAULT ECAM caution: 

- No specific crew action is requested by the WHEEL N/W STRG FAULT ECAM caution 

procedure. 

- Refer to the ECAM STATUS." 

 Note 1: When a statement identical to that in paragraph (h) of this AD has been included in the 

general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of 

this AD may be removed from the AFM. 

New Requirements of This AD 

Inspection Thresholds 

 (i) For airplanes that are not specified in paragraph (g) of this AD, at the earlier of the times 

specified in paragraphs (i)(1) and (i)(2) of this AD: Do a special detailed inspection (boroscopic) for 

broken or cracked NLG upper support lugs and missing cylinder lugs, and do all applicable related 

investigative/corrective actions before further flight. Do all actions in accordance with Airbus 

Technical Note 957.1901/05, dated October 18, 2005; or the Accomplishment Instructions of Airbus 

Service Bulletin A320-32-1310, dated February 8, 2006. After the effective date of this AD, only 

Airbus Service Bulletin A320-32-1310, dated February 8, 2006, may be used. Where the service 

bulletin specifies that restoring the NLG is necessary in accordance with Airbus recommendations, 

this AD requires restoring the NLG in accordance with a method approved by the Manager, 

International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation 

Safety Agency (EASA) (or its delegated agent). Repeat the inspection thereafter at the applicable 

interval specified in paragraph (j) or (k) of this AD. 
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 (1) Within 100 flight cycles following an electronic centralized aircraft monitoring (ECAM) 

caution ''L/G SHOCK ABSORBER FAULT'' associated with at least one of the following centralized 

fault display system (CFDS) messages specified in paragraph (i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this 

AD. 

 (i) ''N L/G EXT PROX SNSR 24GA TGT POS.'' 

 (ii) ''N L/G EXT PROX SNSR 25GA TGT POS.'' 

 (iii) ''N L/G SHOCK ABSORBER FAULT 2526GM.'' 

 (2) At the later of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD. 

 (i) Within 20 months, 6,000 flight hours, or 4,500 flight cycles since the date of issuance of the 

original French standard airworthiness certificate, or the original French export certificate of 

airworthiness, whichever occurs first. 

 (ii) Within 6 months, 1,800 flight hours, or 1,350 flight cycles after the effective date of this AD, 

whichever occurs first. 

Repetitive Inspection Intervals 

 (j) For airplanes not specified in paragraph (g) of this AD that are equipped with EMM BSCU 

standard L4.1 or L4.5: Repeat the inspection specified in paragraph (i) of this AD thereafter at 

intervals not to exceed the earliest of 6 months; 1,800 flight hours; 1,350 flight cycles; or 100 flight 

cycles following certain ECAM cautions and CFDS messages, as specified in paragraph (i)(1) of this 

AD. 

 (k) For airplanes not specified in paragraph (g) of this AD that are equipped with EMM BSCU 

standard L4.8 or a non-EMM BSCU: Repeat the inspection specified in paragraph (i) of this AD 

thereafter at intervals not to exceed the earliest of 20 months; 6,000 flight hours; 4,500 flight cycles; 

or 100 flight cycles following certain ECAM cautions and CFDS messages, as specified in paragraph 

(i)(1) of this AD. 

 Note 2: For the purposes of this AD, a special detailed inspection is: ''An intensive examination 

of a specific item, installation, or assembly to detect damage, failure, or irregularity. The examination 

is likely to make extensive use of specialized inspection techniques and/or equipment. Intricate 

cleaning and substantial access or disassembly procedure may be required.'' 

Optional Terminating Action 

 (l) For airplanes that are not specified in paragraph (g) of this AD: Installation of an NLG with 

new upper support anti-rotation lugs and new cylinder lugs, or installation of an NLG that was never 

driven by EMM BSCU standard L4.1 or L4.5; combined with installation of an EMM BSCU 

standard L4.8 or a non-EMM BSCU; constitutes terminating action for the requirements of this AD. 

Do the installations in accordance with a method approved by either the Manager, International 

Branch, ANM-116; or the EASA (or its delegated agent). Chapter 32 of the Airbus 

A318/A319/A320/A321 Aircraft Maintenance Manual (AMM) is one approved method for doing the 

installations. 

No Report Required 

 (m) Although Airbus Service Bulletin A320-32-1310, dated February 8, 2006, specifies sending 

certain inspection results to Airbus, this AD does not include that requirement. 
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Credit Paragraph 

 (n) Inspections done before the effective date of this AD in accordance with Chapter 12, Subject 

12-14-32 of the Airbus A318/A319/A320/A321 AMM, as revised by Airbus A318/A319/A320/A321 

AMM Temporary Revision 12-001, dated November 13, 2005, are acceptable for compliance with 

the requirements of paragraph (i) of this AD. 

Alternative Methods of Compliance (AMOCs) 

 (o)(1) The Manager, International Branch, ANM-116, 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. 

Related Information 

 (p) EASA airworthiness directive 2006-0174, dated June 21, 2006, also addresses the subject of 

this AD. 

Material Incorporated by Reference

 (q) You must use Airbus Technical Note 957.1901/05, dated October 18, 2005; or Airbus 

Service Bulletin A320-32-1310, dated February 8, 2006; as applicable, to perform the actions that are 

required by this AD, unless the AD specifies otherwise. 

 (1) The Director of the Federal Register approved the incorporation by reference of Airbus 

Service Bulletin A320-32-1310, dated February 8, 2006, in accordance with 5 U.S.C. 552(a) and 1 

CFR part 51. 

 (2) On November 30, 2005 (70 FR 70715, November 23, 2005), the Director of the Federal 

Register approved the incorporation by reference of Airbus Technical Note 957.1901/05, dated 

October 18, 2005. 

 (3) 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 August 17, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, Aircraft Certification Service. 

[FR Doc. E7-17385 Filed 9-5-07; 8:45 am]