AD 2003-04-20

[Federal Register Volume 68, Number 40 (Friday, February 28, 2003)]
[Rules and Regulations]
[Pages 9521-9523]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-4586]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-15-AD; Amendment 39-13069; AD 2003-04-20]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Raytheon Model DH.125, HS.125, BH.125, and 
BAe.125 (U-125 and C-29A) series airplanes; and Model Hawker 800, 
Hawker 800 (including variant U-125A), Hawker 800XP, and Hawker 1000 
airplanes; that currently requires an inspection for cracking or 
corrosion of the cylinder head lugs of the main landing gear (MLG) 
actuator and follow-on/corrective actions. This amendment expands the 
applicability of the existing AD to add an airplane model and further 
clarify the applicability and, for certain airplanes, to clarify the 
compliance time of the inspection requirements. This action is 
necessary to prevent separation of the cylinder head lugs, which could 
prevent the MLG from extending and result in a partial gear-up landing. 
This action is intended to address the identified unsafe condition.

DATES: Effective April 4, 2003.
    The incorporation by reference of a certain publication, as 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).

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Aircraft Company, Department 62, PO Box 85, 
Wichita, Kansas 67201-0085. This information may be examined at the 
Federal Aviation Administration (FAA), Transport Airplane Directorate, 
Rules Docket, 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.

[[Page 9522]]


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

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2001-17-26 R1, 
amendment 39-12619 (67 FR 4171, January 29, 2002), which is applicable 
to certain Raytheon Model DH.125, HS.125, BH.125, and BAe.125 (U-125 
and C-29A) series airplanes; and Model Hawker 800, Hawker 800 
(including variant U-125A), Hawker 800XP, and Hawker 1000 airplanes; 
was published in the Federal Register on August 30, 2002 (67 FR 55742). 
The action proposed to continue to require an inspection for cracking 
or corrosion of the cylinder head lugs of the main landing gear (MLG) 
actuator, and follow-on/corrective actions. The action also proposed to 
expand and clarify the applicability of the existing AD per the 
referenced service bulletin and type certificate data sheet, and, for 
certain airplanes, to clarify the compliance time for the inspection 
requirements in paragraph (b)(3) of this AD.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Explanation of Change to Applicability

    For clarification purposes, we have revised the wording in the 
parentheses for Model Hawker 800 airplanes in the applicability 
throughout this AD to read ``(including variant U-125A).''

Conclusion

    After careful review of the available data, we have determined that 
air safety and the public interest require the adoption of the rule 
with the changes previously described. We have determined that these 
changes will neither increase the economic burden on any operator nor 
increase the scope of the AD.

Cost Impact

    There are approximately 1,000 airplanes of the affected design in 
the worldwide fleet. We estimate that 650 airplanes of U.S. registry 
will be affected by this AD.
    The actions that are currently required by AD 2001-17-26 R1, and 
retained in this AD, take approximately 20 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the currently required actions on 
U.S. operators is estimated to be $780,000, or $1,200 per airplane.
    This AD does not add any new actions or requirements, and only 
revises the applicability of the AD by adding an airplane model, 
clarifying the model designations, and clarifying the compliance time 
for the inspection requirements for certain airplanes. Therefore, the 
estimated cost impact for this proposed AD is unchanged from the 
existing AD.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions. However, for affected airplanes within the 
period under the warranty agreement, we have been advised that the 
manufacturer has committed previously to its customers that it will 
bear the cost of replacement parts. We also have been advised that 
manufacturer warranty remedies are available for labor costs associated 
with accomplishing the actions required by this AD. Therefore, the 
future economic cost impact of this AD may be less than the cost impact 
figure indicated above.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    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 39-12619 (67 FR 
4171, January 29, 2002), and by adding a new airworthiness directive 
(AD), amendment 39-13069, to read as follows:

2003-04-20 Raytheon Aircraft Company: Amendment 39-13069. Docket 
2002-NM-15-AD. Supersedes AD 2001-17-26 R1, Amendment 39-12619.

    Applicability: Model DH.125, HS.125, and BH.125 series 
airplanes; Model BAe.125 series 800A, 800A (C-29A), 800A (U-125), 
800B, 1000A, and 1000B airplanes; and Model Hawker 800, 800 
(including variant U-125A), 1000, and 800XP airplanes; as listed in 
Raytheon Service Bulletin 32-3391, dated August 2000; 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 (e) 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:

[[Page 9523]]

    Restatement of Certain Requirements of AD 2001-17-26 R1:

Inspection

    (a) For Model DH.125, HS.125, and BH.125 series airplanes; 
BAe.125 series 800A, 800A (C-19A), 800A (U-125A), 1000A, and 1000B 
airplanes; and Model Hawker 800, 800 (including variant U-125A), 
800XP, and 1000 airplanes: 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 October 3, 2001 (the effective date of AD 2001-17-26 
R1, amendment 39-12619): Perform the eddy current inspection within 
24 months after October 3, 2001.
    (2) For actuator cylinder heads that have 3,001 to 4,000 total 
landings as of October 3, 2001: Perform the eddy current inspection 
within 6 months after October 3, 2001.
    (3) For actuator cylinder heads that have been in service for 
more than 7 years as of October 3, 2001: Perform the eddy current 
inspection within 6 months after October 3, 2001.
    (4) For actuator cylinder heads that have 4,001 or more total 
landings as of October 3, 2001: Perform the eddy current inspection 
within 10 landings after October 3, 2001.
    New Requirements of this AD:
    (b) For Model BAe.125 series 800B airplanes: 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 (b)(1), (b)(2), or (b)(3) 
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 or that have 4,001 or more total landings as of 
the effective date of this AD: Perform the eddy current inspection 
at the earlier of the times specified in paragraph (b)(3)(i) or 
(b)(3)(ii) of this AD.
    (i) Within 6 months after the effective date of this AD.
    (ii) Within 10 landings after the effective date of this AD.

If No Cracking or Corrosion

    (c) If no cracking or corrosion is found during the inspection 
required by paragraph (a) or (b) of this AD, before further flight, 
accomplish follow-on actions (e.g., ``vibro-etching'' the MLG 
actuator data plate, painting a blue stripe on the actuator cylinder 
head to indicate 1\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

    (d) If any cracking or corrosion is found during the inspection 
required by paragraph (a) or (b) of this AD, before further flight, 
accomplish either of the actions specified in paragraph (d)(1) or 
(d)(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 Component Maintenance Manual 32-30-
1105 as an additional source of service information.

Alternative Methods of Compliance

    (e) 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 Permits

    (f) 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

    (g) The actions shall be done in accordance with Raytheon 
Service Bulletin 32-3391, dated August 2000. This incorporation by 
reference of that document 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, Mid-Continent 
Airport, Wichita, Kansas; or at the Office of the Federal Register, 
800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (h) This amendment becomes effective on April 4, 2003.

    Issued in Renton, Washington, on February 19, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-4586 Filed 2-27-03; 8:45 am]
BILLING CODE 4910-13-P