Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes

[Federal Register Volume 65, Number 212 (Wednesday, November 1, 2000)]
[Rules and Regulations]
[Pages 65258-65260]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-27791]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-69-AD; Amendment 39-11906; AD 2000-19-05]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-100, -200, -200C, -
300, -400, and -500 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This document corrects information in an existing 
airworthiness directive (AD) that applies to certain Boeing Model 737-
100, -200, -200C, -300, -400, and -500 series airplanes. That AD 
supersedes AD 99-05-15, amendment 39-11063, to require a one-time 
inspection of the attachment nuts at each end attachment of the 
elevator tab push rods to measure run-on torque values, and corrective 
actions, if necessary. That AD also requires replacement of all 
existing bolts and attachment nuts at the forward and aft end 
attachment of each elevator tab push rod with new bolts and self-
locking castellated nuts with cotter pins. This document corrects an 
inadvertent error regarding the compliance time for certain 
requirements of that AD. This correction is necessary to provide an 
adequate compliance time for the replacement of certain parts.

DATES: Effective October 25, 2000.
    The incorporation by reference of Boeing Service Letter 737-SL-27-
118-D, dated December 17, 1999, was approved previously by the Director 
of the Federal Register as of October 25, 2000 (65 FR 56783, September 
20, 2000).
    The incorporation by reference of Boeing Alert Service Bulletin 
737-27A1205, dated August 28, 1997, was approved previously by the 
Director of

[[Page 65259]]

the Federal Register as of March 23, 1999 (64 FR 10935, March 8, 1999).

FOR FURTHER INFORMATION CONTACT: Scott Fung, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1221; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: On September 12, 2000, the Federal Aviation 
Administration (FAA) issued AD 2000-19-05, amendment 39-11906 (65 FR 
56783, September 20, 2000), which applies to certain Boeing Model 737-
100, -200, -200C, -300, -400, and -500 series airplanes. That AD 
supersedes AD 99-05-15, amendment 39-11063, to require a one-time 
inspection of the attachment nuts at each end attachment of the 
elevator tab push rods to measure run-on torque values, and corrective 
actions, if necessary. That AD also requires replacement of all 
existing bolts and attachment nuts at the forward and aft end 
attachment of each elevator tab push rod with new bolts and self-
locking castellated nuts with cotter pins. That AD was prompted by 
reports of excessive high-frequency airframe vibration during flight, 
with consequent structural damage to the elevator tab, elevator, and 
stabilizer. The actions required by that AD are intended to prevent 
detachment of an elevator tab push rod due to a detached nut at either 
end attachment of a push rod, which could result in excessive high-
frequency airframe vibration during flight; consequent structural 
damage to the elevator tab, elevator, and horizontal stabilizer; and 
reduced controllability of the airplane.

Need for the Correction

    Since the issuance of AD 2000-19-05, the FAA has reviewed the 
wording in paragraph (b) of that AD and finds that there was an 
inadvertent error in the compliance time. In the preamble of AD 2000-
19-05, the FAA concurred with a commenter's request to extend the 
compliance time in paragraph (b) from, ``Within 12 months or 4,000 
flight cycles after the effective date of this AD, whichever occurs 
first: * * *'' to ``Within 24 months or 4,000 flight cycles after the 
effective date of this AD, whichever occurs first: * * *'' However, in 
the final rule the FAA inadvertently retained the proposed compliance 
time of ``Within 12 months * * *'' This AD corrects the compliance time 
for paragraph (b) of that AD to read, ``Within 24 months or 4,000 
flight cycles after the effective date of this AD, whichever occurs 
first: * * *''

Correction of Publication

    This document corrects the error and correctly adds the AD as an 
amendment to Sec. 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 October 25, 2000.
    Since this action only corrects an error, which extends the 
compliance time in that AD, 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 Subject 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  [Corrected]

    2. Section 39.13 is amended by correctly adding the following 
airworthiness directive (AD):

2000-19-05  Boeing: Amendment 39-11906. Docket 99-NM-69-AD. 
Supersedes AD 99-05-15, Amendment 39-11063.

    Applicability: Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes; line numbers 1 through 2939 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)(1) 
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 prevent detachment of an elevator tab push rod due to a 
detached nut at either end attachment of a push rod, which could 
result in excessive high-frequency airframe vibration during flight; 
consequent structural damage to the elevator tab, elevator, and 
horizontal stabilizer; and reduced controllability of the airplane; 
accomplish the following:

Restatement of Requirements of AD 99-05-15

One-Time Inspection

    (a) Within 90 days after March 23, 1999 (the effective date of 
AD 99-05-15, amendment 39-11063): Perform a one-time inspection of 
all attachment nuts at each end of each elevator tab push rod to 
measure the run-on torque values of the nuts, in accordance with 
Boeing Alert Service Bulletin 737-27A1205, dated August 28, 1997.

Corrective Actions

    (1) If the run-on torque value of any end attachment nut is 
within the limits specified in the alert service bulletin, prior to 
further flight, ensure that the final seating torque of the 
attachment nuts is within the torque values specified in the alert 
service bulletin.
    (2) If the run-on torque value of any end attachment nut is 
outside the limits specified in the alert service bulletin, prior to 
further flight, replace all existing bolts and attachment nuts at 
each end of each elevator tab push rod with new bolts and self-
locking castellated nuts that have cotter pins installed as a 
secondary locking feature, in accordance with Boeing Service Letter 
737-SL-27-118-D, dated December 17, 1999, and ensure that the final 
seating torque of the nuts is within the torque values specified in 
the service letter.

    Note 2: Accomplishment of the inspection and ensuring adequate 
final seating torque values prior to the effective date of this AD 
in accordance with Boeing All-Base Telex M-7272-97-0897, dated 
February 13, 1997, are considered acceptable for compliance with the 
actions specified in paragraphs (a) and (a)(1) of this AD for only 
the forward attachment nuts.

New Requirements of This AD

Replacement

    (b) Within 24 months or 4,000 flight cycles after the effective 
date of this AD, whichever occurs first: Replace all existing bolts 
and attachment nuts at the forward and aft end attachment of each 
elevator tab push rod with new bolts and self-locking castellated 
nuts that have cotter pins installed as a secondary locking feature, 
in accordance with Boeing Service Letter 737-SL-27-118-D, dated 
December 17, 1999.

    Note 3: Replacements accomplished prior to the effective date of 
this AD in accordance

[[Page 65260]]

with Boeing Service Letter 737-SL-27-118-A, dated November 14, 1997; 
737-SL-27-118-B, dated April 14, 1999; or 737-SL-27-118-C, dated May 
19, 1999; are considered acceptable for compliance with paragraphs 
(a)(2) and (b) of this AD.

Alternative Methods of Compliance

    (c)(1) 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, Seattle Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 99-05-15, amendment 39-11063, are considered to 
be approved as alternative methods of compliance with paragraph (a) 
of this AD only.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Secs. 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) The actions shall be done in accordance with Boeing Alert 
Service Bulletin 737-27A1205, dated August 28, 1997, and Boeing 
Service Letter 737-SL-27-118-D, dated December 17, 1999.
    (1) The incorporation by reference of Boeing Service Letter 737-
SL-27-118-D, dated December 17, 1999, was approved previously by the 
Director of the Federal Register as of October 25, 2000 (65 FR 
56783, September 20, 2000).
    (2) The incorporation by reference of Boeing Alert Service 
Bulletin 737-27A1205, dated August 28, 1997, was approved previously 
by the Director of the Federal Register as of March 23, 1999 (64 FR 
10935, March 8, 1999).
    (3) Copies may be obtained from Boeing Commercial Airplane 
Group, P.O. Box 3707, Seattle, Washington 98124-2207. 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.
    (f) The effective date of this amendment remains October 25, 
2000.

    Issued in Renton, Washington, on October 24, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-27791 Filed 10-31-00; 8:45 am]
BILLING CODE 4910-13-P

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