Airworthiness Directives; Saab Model SAAB SF340A and SAAB 340B Series Airplanes

[Federal Register Volume 67, Number 3 (Friday, January 4, 2002)]
[Rules and Regulations]
[Pages 500-501]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-85]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-91-AD; Amendment 39-12576; AD 2001-23-12 R1]
RIN 2120-AA64


Airworthiness Directives; Saab Model SAAB SF340A and SAAB 340B 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This document revises an existing airworthiness directive (AD) 
that applies to certain Saab Model SAAB SF340A and SAAB 340B series 
airplanes. That AD currently requires a one-time review of records to 
determine whether an airplane has been repainted since its delivery 
from the factory; and a one-time inspection to detect damage associated 
with improper preparation for the repainting, and corrective action if 
necessary. The actions specified in that AD are intended to detect and 
correct damage to the aluminum skin of the airplane, which could result 
in a weakening of the structure of the airplane. This document corrects 
certain conditional requirements of the existing AD.

DATES: Effective December 31, 2001.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of December 31, 2001 (66 FR 58927, November 26, 2001).

FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1175; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: On November 15, 2001, the FAA issued AD 
2001-23-12, amendment 39-12511 (66 FR 58927, November 26, 2001), 
applicable to certain Saab Model SAAB SF340A and SAAB 340B series 
airplanes, to require a one-time review of records to determine whether 
an airplane has been repainted since its delivery from the factory; and 
a one-time inspection to detect damage associated with improper 
preparation for the repainting, and corrective action if necessary. 
That action was prompted by mandatory continuing airworthiness 
information from a foreign civil airworthiness authority. The 
requirements of that AD are intended to detect and correct damage to 
the aluminum skin of the airplane, which could result in a weakening of 
the structure of the airplane.

Need for the Correction

    Information obtained recently by the FAA indicates that the final 
rule of this AD conveyed an inaccurate interpretation of a comment 
submitted on the proposed AD. The commenter had requested that 
paragraph ``(B)(2)'' of the proposed AD be revised to include a 
corrective action to immediately repaint the stripped areas, and to 
extend the compliance time to strip and repaint the airplane. As 
discussed in the response to the comments in AD 2001-23-12, the FAA 
concurred with the request and incorporated that instruction. However, 
the instruction was added to subparagraph (b)(2) when it appears the 
commenter intended the instruction to be inserted into subparagraph 
(b)(2)(ii)(B)(2).
    The FAA has determined that a correction to AD 2001-23-12 is 
necessary. Under the current requirements of subparagraph (b)(2) of the 
AD, affected airplanes are allowed to operate for an additional 4,000 
flight hours or 2 years with inadequate protective coating, which could 
subject the airplanes to damage (or further damage). This correction 
removes the requested language from subparagraph (b)(2) of the AD and 
incorporates the instruction into subparagraph (b)(2)(ii)(B)(2) to 
specify immediate repair of damage and delay the requirement to strip 
and repaint the airplane.
    To clarify the 4,000-flight-hour/2-year compliance time for this 
conditional requirement, the FAA has added the phrase, ``whichever 
occurs first.''
    In addition, the FAA has been advised that subparagraph 
(b)(2)(ii)(B)(2) of the proposed AD inaccurately specifies that the 
entire airplane must be repainted if damage is detected during the 
inspection and if an unapproved paint system had been used. The service 
bulletin specifies that the entire airplane must not be stripped and 
repainted if damage is found in only a certain section of the 
airplane--except for the forward and rear fuselage, stabilizer, and 
wing, which must always be stripped and repainted in total if any 
damage is found within the respective inspection area. The FAA did not 
intend that this AD differ from the service bulletin in that regard. 
This correction revises subparagraph (b)(2)(ii)(B)(2) to clarify the 
conditional requirement by referring to the service bulletin.

[[Page 501]]

Correction of Publication

    This document corrects these errors and correctly adds the AD as an 
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 
39.13). The AD is reprinted in its entirety for the convenience of 
affected operators. The effective date of the AD remains December 31, 
2001.
    Since this action only corrects current requirements, it has no 
adverse economic impact and imposes no additional burden on any person. 
Therefore, the FAA has determined that notice and public procedures are 
unnecessary.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Correction

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-12511 (66 FR 
58927, November 26, 2001), and by adding a new airworthiness directive 
(AD), amendment 39-12576, to read as follows:

2001-23-12 R1  Saab Aircraft AB: Amendment 39-12576. Docket 2001-NM-
91-AD. Revises AD 2001-23-12, Amendment 39-12511.

    Applicability: Model SAAB SF340A series airplanes having serial 
numbers -004 through -159 inclusive, and SAAB 340B series airplanes 
having serial numbers -160 through -459 inclusive; certificated in 
any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (c) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct damage to the aluminum skin of the 
airplane, which could result in a weakening of the structure of the 
airplane, accomplish the following:

Review of Records

    (a) Within 2,000 flight hours or 1 year after December 31, 2001 
(the effective date of AD 2001-23-12, amendment 39-12511), whichever 
occurs first: Perform a review of records to determine whether an 
airplane subject to this AD has been repainted since its delivery 
from the factory. If the airplane has not been repainted, no further 
action is needed.

Inspection and Corrective Action

    (b) If an airplane has been repainted since its delivery from 
the factory: Within 2,000 flight hours or 1 year after December 31, 
2001, whichever occurs first, perform chemical stripping of local 
areas of the skin and inspection to detect damage to (or removal of) 
the protective coat of bonding primer, in accordance with Saab 
Service Bulletin 340-51-020, Revision 01, dated May 16, 2001.
    (1) If no damage to the protective coat of bonding primer is 
detected: Prior to further flight, repaint the stripped areas, in 
accordance with the service bulletin.
    (2) If damage to (or removal of) the protective coat of bonding 
primer is detected: Prior to further flight, perform additional 
chemical stripping and inspection of the skin for pitting corrosion, 
in accordance with the service bulletin.
    (i) If pitting corrosion is detected: Perform corrective action 
in a manner and within a compliance time approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
or the Luftfartsverket (or its designated agent).
    (ii) If no pitting corrosion is detected: Prior to further 
flight, measure the thickness of the skin of the airplane, in 
accordance with the service bulletin.
    (A) If a reduction in skin thickness is detected: Perform 
corrective action in a manner and within a compliance time approved 
by the Manager, International Branch, ANM-116, or the 
Luftfartsverket (or its designated agent).
    (B) If no reduction in skin thickness is detected: Prior to 
further flight, check records to determine whether the airplane was 
repainted using an approved paint system. For purposes of this AD, 
criteria for an ``approved'' paint system are found in section 51-
20-43 of the Saab 340 Structural Repair Manual.
    (1) If the airplane was repainted using an approved paint 
system: Prior to further flight, repaint the stripped areas of the 
airplane, in accordance with the service bulletin.
    (2) If the airplane was repainted using an unapproved paint 
system: Prior to further flight, repaint the stripped areas in 
accordance with the service bulletin; and within 4,000 flight hours 
or 2 years after detection of the damage or removed protective 
coating, whichever occurs first, chemically strip and repaint the 
airplane as specified by and in accordance with the service 
bulletin.

Alternative Methods of Compliance

    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, International Branch, ANM-116. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, International Branch, ANM-116.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (e) Except as required by paragraphs (a), (b)(2)(i), and 
(b)(2)(ii)(A) of this AD: The actions shall be done in accordance 
with Saab Service Bulletin 340-51-020, Revision 01, dated May 16, 
2001. This incorporation by reference was approved previously by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51 as of December 31, 2001 (66 FR 58927, November 26, 
2001). Copies may be obtained from Saab Aircraft AB, SAAB Aircraft 
Product Support, S-581.88, Linkoping, Sweden. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in Swedish 
airworthiness directive SAD 1-161R2, dated March 13, 2001.

Effective Date

    (f) The effective date of this amendment remains December 31, 
2001.

    Issued in Renton, Washington, on December 20, 2001.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-85 Filed 1-3-02; 8:45 am]
BILLING CODE 4910-13-U

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