Airworthiness Directives; Sabreliner Model NA-265, NA-265-20, NA-265-30, NA-265-40, NA-265-50, NA-265-60, NA-265-65, NA-265-70, and NA-265-80 Series Airplanes

[Federal Register Volume 70, Number 239 (Wednesday, December 14, 2005)]
[Rules and Regulations]
[Pages 73923-73925]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-23904]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22402; Directorate Identifier 2005-NM-133-AD; 
Amendment 39-14411; AD 2005-25-18]
RIN 2120-AA64


Airworthiness Directives; Sabreliner Model NA-265, NA-265-20, NA-
265-30, NA-265-40, NA-265-50, NA-265-60, NA-265-65, NA-265-70, and NA-
265-80 Series 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 certain Sabreliner Model NA-265-40, NA-265-50, 
NA-265-60, NA-265-70, and NA-265-80 series airplanes. That AD currently 
requires repetitive inspections for discrepancies in the front and rear 
spars of the wing in the area of the wing center section, and in the 
lugs on the rear spar and wing trailing edge panel rib, and corrective 
actions if necessary. This new AD expands the applicability of the 
existing AD and requires new repetitive inspections for fuel leaks of 
the front and rear spars of the wing, and for discrepancies in the 
front and rear spars of the wing in the area of the wing center 
section, and in the lugs on the rear spar and wing trailing edge panel 
rib. This AD also requires related investigative and corrective 
actions, if necessary. This AD results from reports of cracking in the 
upper and lower flanges of the front and rear spars of the wing near 
the wing center section, and in the lugs on the rear spar. We are 
issuing this AD to detect and correct cracking or other discrepancies 
in these areas, which could result in structural failure of the wing.

DATES: This AD becomes effective January 18, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of January 18, 
2006.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Sabreliner Corporation, 18118 Chesterfield Airport Road, 
Chesterfield, Missouri 63005-1121, for service information identified 
in this AD.

FOR FURTHER INFORMATION CONTACT: T.N. Baktha, Aerospace Engineer, 
Airframe Branch, ACE-118W, FAA, Wichita Aircraft Certification Office, 
1801 Airport Road, room 100, Mid-Continent Airport, Wichita, Kansas 
67209; telephone (316) 946-4155; fax (316) 946-4407.

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 Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the 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 73-18-03, amendment 39-
3201 (43 FR 19208, May 4, 1978). The existing AD applies to certain 
Rockwell International Model NA-265-40, NA-265-50, NA-265-60, NA-265-
70, and NA-265-80 series airplanes. That NPRM was published in the 
Federal Register on September 14, 2005 (70 FR 54318). (A correction of 
that NPRM was published in the Federal Register on September 30, 2005 
(70 FR 57222).) That NPRM proposed to expand the applicability of the 
existing AD and require new repetitive inspections for fuel leaks of 
the front and rear spars of the wing, and for discrepancies in the 
front and rear spars of the wing in the area of the wing center 
section, and in the lugs on the rear spar and wing trailing edge panel 
rib. That NPRM also proposed to require related investigative and 
corrective actions, if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the NPRM or 
on the determination of the cost to the public.

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 and determined that 
air safety and the public interest require adopting the AD with the 
change described previously. We have determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

Costs of Compliance

    There are about 77 airplanes of the affected design in the 
worldwide fleet. This AD affects about 43 airplanes of U.S. registry.
    The inspection specified in this AD takes about 12 work hours per 
airplane, per inspection cycle, at an average labor rate of $65 per 
work hour. Based on these figures, the estimated cost of the actions 
specified in this AD for U.S. operators is $33,540, or $780 per 
airplane, 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.
    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.

[[Page 73924]]

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

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 39-3201 (43 FR 19208, May 4, 1978) and by adding the 
following new airworthiness directive (AD):

2005-25-18 Sabreliner Corporation: Amendment 39-14411. Docket No. 
FAA-2005-22402; Directorate Identifier 2005-NM-133-AD.

Effective Date

    (a) This AD becomes effective January 18, 2006.

Affected ADs

    (b) This AD supersedes AD 73-18-03.

Applicability

    (c) This AD applies to Sabreliner Model NA-265, NA-265-20, NA-
265-30, NA-265-40, NA-265-50, NA-265-60, NA-265-65, NA-265-70, and 
NA-265-80 series airplanes; certificated in any category; as 
identified in Sabreliner NA-265 Service Bulletin 83-2, revised 
January 31, 2005.

Unsafe Condition

    (d) This AD results from reports of cracking in the upper and 
lower flanges of the front and rear spars of the wing near the wing 
center section, and in the lugs on the rear spar. The FAA is issuing 
this AD to detect and correct cracking or other discrepancies in 
these areas, which could result in structural failure of the wing.

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.

Requirements of AD 73-18-03

Repetitive Inspections

    (f) For the airplanes listed in Table 1 of this AD: On or before 
June 18, 1974, unless previously accomplished within 1 year, and at 
intervals not to exceed 2 years thereafter until the first 
inspection in accordance with paragraph (j) of this AD has been 
done, inspect the upper and lower flanges of the front and rear 
spars in the area of the wing center section, and the lugs on the 
rear spar and wing trailing edge panel rib, per the instructions of 
Sabreliner NA-265 Service Bulletin 73-11, revised June 1, 1978; or 
an equivalent inspection approved by the Manager, Wichita Aircraft 
Certification Office (ACO), FAA. Inspections done before the 
effective date of this AD in accordance with Sabreliner NA-265 
Service Bulletin 73-11, dated June 15, 1973, are acceptable for 
compliance with this paragraph.

 Table 1.--Airplanes Subject to Paragraphs (f), (g), and (h) of this AD
------------------------------------------------------------------------
                Model                       Affected serial numbers
------------------------------------------------------------------------
NA-265-40...........................  282-1 and subsequent.
NA-265-50...........................  287-1.
NA-265-60...........................  306-1 through 306-139 inclusive.
NA-265-70...........................  370-1 through 370-9 inclusive.
NA-265-80...........................  380-1 through 380-61 inclusive.
------------------------------------------------------------------------

Corrective Actions

    (g) For the airplanes listed in Table 1 of this AD: Prior to 
further flight, if cracks, corrosion, or breaks in the surface 
finish are found, during any inspection in accordance with paragraph 
(f) of this AD, in the front or rear spars in the area of the wing 
center section, replace with like serviceable parts, or repair in a 
manner approved by the Manager, Wichita ACO.
    (h) For the airplanes listed in Table 1 of this AD: Prior to 
further flight, if cracks are found, during any inspection in 
accordance with paragraph (f) of this AD, in the lugs on the rear 
spar and wing trailing edge rib, replace the cracked parts with like 
serviceable parts, or repair in a manner approved by the Manager, 
Wichita ACO.

New Requirements of This AD

Inspections/Repairs Accomplished Previously

    (i) Inspections and repairs accomplished before the effective 
date of this AD in accordance with a method approved by the Chief, 
Aircraft Engineering Division, FAA Western Region, are acceptable 
for compliance with paragraphs (f), (g), and (h) of this AD, as 
applicable.

New Repetitive Inspections

    (j) Within 90 days after the effective date of this AD, except 
as provided by paragraph (j)(1) of this AD: Perform a general visual 
inspection for fuel leaks; an inspection using a borescope to detect 
any break in the surface finish, corrosion, or cracking of the upper 
and lower flanges on the front and rear spars of the wing in the 
area of the wing center section; a general visual inspection to 
detect cracking of the lugs on the rear spar and wing trailing edge 
panel rib; and related investigative actions, as applicable; by 
doing all applicable actions in accordance with the instructions of 
Sabreliner NA-265 Service Bulletin 83-2, revised January 31, 2005. 
Repeat the inspection thereafter at intervals not to exceed 24 
months.
    (1) If the inspection required by paragraph (j) of this AD has 
been accomplished within 12 months before the effective date of this 
AD, the inspection required by paragraph (j) of this AD is not 
required until 24 months after the most recent inspection in 
accordance with the requirements of paragraph (j) of this AD.
    (2) For airplanes subject to paragraph (f) of this AD: 
Accomplishing of the initial inspection required by paragraph (j) of 
this AD terminates the requirements of paragraph (f) of this AD.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

Corrective Actions

    (k) If any fuel leak, break in the surface finish, corrosion, or 
cracking is found during any inspection required by paragraph (j) of 
this AD: Before further flight, replace the subject part with a new 
or serviceable part, or repair the subject part in accordance with a 
method approved by the Manager, Wichita ACO. Where Sabreliner NA-265 
Service Bulletin 83-2, revised January 31, 2005, specifies 
contacting Sabreliner for an engineering analysis: Before further 
flight, repair in accordance with a method approved by the Manager, 
Wichita ACO. For a repair method to be approved by the Manager, 
Wichita ACO, as required by this paragraph,

[[Page 73925]]

the Manager's approval letter must specifically refer to this AD.

Actions Accomplished Previously

    (l) Inspections and corrective actions accomplished before the 
effective date of this AD in accordance with the original issue of 
Sabreliner NA-265 Service Bulletin 83-2, dated March 4, 1983; or 
Sabreliner NA-265 Service Bulletin 83-2, revised February 29, 1996; 
are acceptable for compliance with the corresponding actions 
required by paragraphs (j) and (k) of this AD.

No Reporting Requirement

    (m) Although the service bulletins referenced in this AD specify 
to submit certain information to the manufacturer, this AD does not 
include that requirement.

Alternative Methods of Compliance (AMOCs)

    (n)(1) The Manager, Wichita ACO, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Material Incorporated by Reference

    (o) You must use Sabreliner NA-265 Service Bulletin 73-11, 
revised June 1, 1978; or Sabreliner NA-265 Service Bulletin 83-2, 
revised January 31, 2005; to perform the actions that are required 
by this AD, unless the AD specifies otherwise. Sabreliner NA-265 
Service Bulletin 73-11, revised June 1, 1978, contains the following 
effective pages:

------------------------------------------------------------------------
                Page No.                        Date shown on page
------------------------------------------------------------------------
1......................................  June 1, 1978.
2-14...................................  June 15, 1973.
------------------------------------------------------------------------

    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 Sabreliner Corporation, 18118 
Chesterfield Airport Road, Chesterfield, Missouri 63005-1121, for a 
copy of this service information. You may review copies at the 
Docket Management Facility, U.S. Department of Transportation, 400 
Seventh Street SW., Room PL-401, Nassif Building, Washington, DC; on 
the Internet at http://dms.dot.gov; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 2, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-23904 Filed 12-13-05; 8:45 am]
BILLING CODE 4910-13-P

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