Airworthiness Directives; Raytheon Model DH.125, HS.125, BH.125, and BAe.125 (U-125 and C-29A) Series Airplanes; Model Hawker 800, Hawker 800 (U-125A), Hawker 800XP, and Hawker 1000 Airplanes

[Federal Register Volume 67, Number 19 (Tuesday, January 29, 2002)]
[Rules and Regulations]
[Pages 4171-4172]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-1966]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-373-AD; Amendment 39-12619; AD 2001-17-26 R1]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model DH.125, HS.125, BH.125, 
and BAe.125 (U-125 and C-29A) Series Airplanes; Model Hawker 800, 
Hawker 800 (U-125A), Hawker 800XP, and Hawker 1000 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This document corrects and clarifies information in an 
existing airworthiness directive (AD) that applies to certain Raytheon 
Model DH.125, HS.125, BH.125, and BAe.125 (U-125 and C-29A) series 
airplanes; Model Hawker 800, Hawker 800 (U-125A), Hawker 800XP, and 
Hawker 1000 airplanes. That AD currently requires an inspection for 
cracking or corrosion of the cylinder head lugs of the main landing 
gear actuator and follow-on/corrective actions. This document corrects 
and clarifies the affected airplane serial numbers. This correction is 
necessary to ensure that operators do not misinterpret which airplanes 
are subject to the requirements of this AD.

DATES: Effective October 3, 2001.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of October 3, 2001 (66 FR 45575, August 29, 2001).

FOR FURTHER INFORMATION CONTACT: David Ostrodka, Aerospace Engineer, 
Airframe Branch, ACE-118W, FAA, Wichita Aircraft Certification Office, 
1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone (316) 
946-4129; fax (316) 946-4407.

SUPPLEMENTARY INFORMATION: On August 20, 2001, the Federal Aviation 
Administration (FAA) issued AD 2001-17-26, amendment 39-12417 (66 FR 
45575, August 29, 2001), which applies to certain Raytheon Model 
DH.125, HS.125, BH.125, and BAe.125 (U-125 and C-29A) series airplanes; 
Model Hawker 800, Hawker 800 (U-125A), Hawker 800XP, and Hawker 1000 
airplanes. That AD requires an inspection for cracking or corrosion of 
the cylinder head lugs of the main landing gear (MLG) actuator and 
follow-on/corrective actions. That AD was prompted by reports of 
attachment lugs cracking at the actuator cylinder head. The actions 
required by that AD are intended to prevent separation of the cylinder 
head lugs, which could prevent the main landing gear from extending and 
result in a partial gear-up landing.

Need for the Correction

    Information obtained recently by the FAA indicates that the 
applicability of AD 2001-17-26 needs to be clarified and corrected.
    As published, the applicability of that AD did not include the 
serial numbers of certain airplane models that were cited in the 
effectivity of Raytheon Service Bulletin 32-3391, dated August 2000. To 
correct that omission, we have determined that the applicability of 
this AD also must include the affected airplane serial numbers for 
Model Hawker 800 (U-125A up to and including serial number 258381) and 
for Model Hawker 800XP (up to but not including serial number 258490), 
as cited in the service bulletin.
    Although the applicability of AD 2001-17-26 did not include the 
serial numbers, the FAA's intent was to list the serial numbers cited 
in the referenced service bulletin.
    The FAA has determined that a correction to AD 2001-17-26 is 
necessary to correct and clarify the applicability and to include the 
affected airplane serial numbers.

Correction of Publication

    This document corrects and clarifies the errors of AD 2001-17-26 
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 October 3, 2001.

[[Page 4172]]

    Since this action only clarifies and corrects a current 
requirement, 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):

2001-17-26  R1 Raytheon Aircraft Company: Amendment 39-12619. Docket 
2000-NM-373-AD: Revises AD 2001-17-26, Amendment 39-12417.

    Applicability: Model DH.125, HS.125, BH.125, and BAe.125 (U-125 
and C-29A) series airplanes; Model Hawker 800, Hawker 800 (U-125A up 
to and including serial number 258381), Hawker 800XP (up to but not 
including serial number 258490), and Hawker 1000 airplanes; 
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 (d) 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 separation of the cylinder head lugs, which could 
prevent the main landing gear (MLG) from extending and result in a 
partial gear-up landing, accomplish the following:

Inspection

    (a) Perform an eddy current inspection of the actuator cylinder 
head lugs for cracking or corrosion per Raytheon Service Bulletin 
32-3391, dated August 2000, at the time specified in paragraph 
(a)(1), (a)(2), (a)(3), or (a)(4) of this AD, as applicable.
    (1) For actuator cylinder heads that have 3,000 or less total 
landings as of the effective date of this AD: Perform the eddy 
current inspection within 24 months after the effective date of this 
AD.
    (2) For actuator cylinder heads that have 3,001 to 4,000 total 
landings as of the effective date of this AD: Perform the eddy 
current inspection within 6 months after the effective date of this 
AD.
    (3) For actuator cylinder heads that have been in service for 
more than 7 years as of the effective date of this AD: Perform the 
eddy current inspection within 6 months of the effective date of 
this AD.
    (4) For actuator cylinder heads that have 4,001 or more total 
landings as of the effective date of this AD: Perform the eddy 
current inspection within 10 landings after the effective date of 
this AD.

If No Cracking or Corrosion

    (b) If no cracking or corrosion is found during the inspection 
required by paragraph (a) of this AD, before further flight, 
accomplish the follow-on actions (e.g., ``vibro-etching'' the MLG 
actuator data plate, painting a blue stripe on the actuator cylinder 
head to indicate \1/32\ inch oversize bushings, replacing bushings, 
and applying corrosion protection to the lug bores), per Raytheon 
Service Bulletin 32-3391, dated August 2000.

If Any Cracking or Corrosion

    (c) If any cracking or corrosion is found during the inspection 
required by paragraph (a) of this AD, before further flight, 
accomplish either of the actions specified in paragraph (c)(1) or 
(c)(2) of this AD, per Raytheon Service Bulletin 32-3391, dated 
August 2000.
    (1) Replace the actuator of the MLG with a new or serviceable 
actuator, or
    (2) Replace the actuator cylinder head with a new cylinder head.

    Note 2: Raytheon Service Bulletin 32-3391, dated August 2000, 
references Precision Hydraulics Cylinder Maintenance Manual (CMM) 
32-30-1105 as an additional source of service information.

Alternative Methods of Compliance

    (d) 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, Wichita 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, Wichita ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

Special Flight Permit

    (e) 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

    (f) The actions shall be done in accordance with Raytheon 
Service Bulletin 32-3391, dated August 2000. This incorporation by 
reference was approved previously by the Director of the Federal 
Register as of October 3, 2001 (66 FR 45575, August 29, 2001). 
Copies may be obtained from Raytheon Aircraft Company, Department 
62, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., 
Renton, Washington; or at the FAA, Wichita Aircraft Certification 
Office, 1801 Airport Road, Room 100, Wichita, Kansas; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

Effective Date

    (g) The effective date of this amendment remains October 3, 
2001.

    Issued in Renton, Washington, on January 18, 2002.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification, 
Service.
[FR Doc. 02-1966 Filed 1-28-02; 8:45 am]
BILLING CODE 4910-13-P

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