[Federal Register Volume 72, Number 172 (Thursday, September 6, 2007)]
[Rules and Regulations]
[Pages 51164-51167]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-17385]


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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.

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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.

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

[[Page 51165]]

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 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     1....................         None  $80.................  $57,600.
 2005-24-06).
AFM revision (required by AD 2005- 1....................         None  $80.................  $57,600.
 24-06).
Special detailed inspection in     1....................         None  $80, per inspection   $57,600, per
 accordance with new service                                            cycle.                inspection cycle.
 information (new action).
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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.

[[Page 51166]]

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14386 (70 FR 70715, November 23, 2005) and by 
adding the following new airworthiness directive (AD):

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.

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.

    [squarf] 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.

    [squarf] 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.
    (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

[[Page 51167]]

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.

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]
BILLING CODE 4910-13-P