[Federal Register Volume 60, Number 2 (Wednesday, January 4, 1995)]
[Rules and Regulations]
[Pages 330-332]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-50]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-137-AD; Amendment 39-9107; AD 94-26-12]


Airworthiness Directives; Raytheon Corporate Jets Model Hawker 
800 and 1000 and Model DH/BH/HS/BAe 125 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Raytheon Corporate Jets Model Hawker 800 and 1000 
and Model DH/BH/HS/BAe 125 series airplanes, that requires inspections 
to detect cracking of the sidestay jack pivots of the main landing 
gear, and replacement of the sidestay jack pivot assemblies with new 
assemblies. This amendment is prompted by a report of fracturing of a 
jack pivot, which resulted in the inability of the main landing gear to 
deploy. The actions specified by this AD are intended to prevent a 
wheels-up landing.

DATES: Effective February 3, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 3, 1995.

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Corporate Jets, Inc., 3 Bishops Square Street, 
Albans Road West, Hatfield, Hertfordshire, AL109NE, United Kingdom. 
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 Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: William Schroeder, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2141; fax (206) 227-1320.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
[[Page 331]] Aviation Regulations (14 CFR part 39) to include an 
airworthiness directive (AD) that is applicable to certain Raytheon 
Corporate Jets Model Hawker 800 and 1000 and Model DH/BH/HS/BAe 125 
series airplanes was published in the Federal Register on September 27, 
1994 (49 FR 49217). That action proposed to require inspections to 
detect cracking of the sidestay jack pivots of the main landing gear, 
and replacement of the sidestay jack pivot assemblies with new 
assemblies.
    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.
    As a result of recent communications with the Air Transport 
Association (ATA) of America, the FAA has learned that, in general, 
some operators may misunderstand the legal effect of AD's on airplanes 
that are identified in the applicability provision of the AD, but that 
have been altered or repaired in the area addressed by the AD. The FAA 
points out that all airplanes identified in the applicability provision 
of an AD are legally subject to the AD. If an airplane has been altered 
or repaired in the affected area in such a way as to affect compliance 
with the AD, the owner or operator is required to obtain FAA approval 
for an alternative method of compliance with the AD, in accordance with 
the paragraph of each AD that provides for such approvals. A note has 
been added to this final rule to clarify this requirement.
    In addition, the FAA has recently reviewed the figures it has used 
over the past several years in calculating the economic impact of AD 
activity. In order to account for various inflationary costs in the 
airline industry, the FAA has determined that it is necessary to 
increase the labor rate used in these calculations from $55 per work 
hour to $60 per work hour. The economic impact information, below, has 
been revised to reflect this increase in the specified hourly labor 
rate.
    After careful review of the available data the FAA has determined 
that air safety and the public interest require the adoption of the 
rule with the changes previously described. The FAA has determined that 
these changes will neither increase the economic burden on any operator 
nor increase the scope of the AD.
    The FAA estimates that 550 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 6 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. The FAA has been advised that the 
manufacturer plans to provide the required parts at no cost to the 
operators. Based on these figures, the total cost impact of the AD on 
U.S. operators is estimated to be $198,000, or $360 per airplane.
    The total 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 regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

94-26-12 Raytheon Corporate Jets, Inc. (Formerly De Havilland; 
Hawker Siddeley; British Aerospace, plc): Amendment 39-9107. Docket 
94-NM-137-AD.

    Applicability: Model Hawker 800 and 1000 series airplanes and 
Model DH/BH/HS/BAe 125-1A through -1000A series airplanes; equipped 
with main landing gear (MLG) sidestay assemblies on which Post-Mod 
252091 steel jack pivots have been installed; 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 use the authority 
provided in paragraph (f) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition; or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent the inability of the MLG to deploy and a consequent 
wheels-up landing, accomplish the following:
    (a) Perform a detailed visual inspection, using a 10X magnifier, 
to detect cracking of the sidestay assembly jack pivot of the left 
and right MLG, in accordance with Raytheon Corporate Jets Service 
Bulletin SB 32-233, dated June 24, 1994, at the latest of the times 
specified in paragraphs (a)(1), (a)(2), or (a)(3) of this AD.
    (1) Within 28 days after the effective date of this AD; or
    (2) Prior to the accumulation of 3,000 total landings on the 
sidestay assembly since new; or
    (3) Prior to the accumulation of 1,000 total landings since 
overhaul of the sidestay assembly.
    (b) If no cracks are found and the sidestay assembly has been 
overhauled prior to the accomplishment of the inspection specified 
in paragraph (a) of this AD: Accomplish the requirements of 
paragraphs (b)(1) and (b)(2) of this AD in accordance with Raytheon 
Corporate Jets Service Bulletin SB 32-233, dated June 24, 1994.
    (1) Repeat the inspection required by paragraph (a) of this AD 
thereafter at intervals not to exceed 1,000 landings.
    (2) Prior to the accumulation of 4,000 total landings on the 
jack pivot assembly since the sidestay assembly was last overhauled, 
or within 300 landings after the effective date of this AD, 
whichever occurs later: Replace the jack pivot assembly with a new 
assembly. [[Page 332]] Thereafter, prior to the accumulation of 
4,000 landings, remove the jack pivot assembly and replace it with a 
new assembly in accordance with the service bulletin.
    (c) If no cracks are found and the sidestay assembly has not 
been overhauled prior to accomplishment of the inspection required 
by paragraph (a) of this AD: Prior to the accumulation of 4,000 
total landings on the jack pivot assembly, or within 300 landings 
after the effective date of this AD, whichever occurs later, replace 
the jack pivot assembly with a new assembly in accordance with 
Raytheon Corporate Jets Service Bulletin SB 32-233, dated June 24, 
1994. Thereafter, prior to the accumulation of 4,000 landings on the 
jack pivot assembly, replace it with a new assembly in accordance 
with the service bulletin.
    (d) If any crack is found that does not exceed the limits 
specified in Raytheon Corporate Jets Service Bulletin SB 32-233, 
dated June 24, 1994, accomplish the requirements of paragraphs 
(d)(1), (d)(2), or (d)(3) of this AD, as applicable, in accordance 
with the service bulletin.
    (1) For sidestay assemblies that have accumulated 4,000 or more 
total landings since new that have been overhauled prior to 
accomplishment of the inspection specified in paragraph (a) of this 
AD: Accomplish paragraphs (d)(1)(i) and (d)(1)(ii) of this AD.
    (i) Repeat the inspection required by paragraph (a) of this AD 
thereafter at intervals not to exceed 100 landings.
    (ii) Prior to the accumulation of 4,000 total landings on the 
jack pivot assembly since the sidestay assembly was last overhauled, 
or within 300 landings after the effective date of this AD, 
whichever occurs later: Replace the jack pivot assembly with a new 
assembly. Thereafter, prior to the accumulation of 4,000 landings on 
the jack pivot assembly, replace it with a new assembly in 
accordance with the service bulletin.
    (2) For any sidestay assemblies that have accumulated 4,000 or 
more total landings since new that have not been overhauled: 
Accomplish paragraphs (d)(2)(i) and (d)(2)(ii) of this AD.
    (i) Repeat the inspection required by paragraph (a) of this AD 
thereafter at intervals not to exceed 100 landings.
    (ii) Within 300 landings after the effective date of this AD, 
replace the jack pivot assembly with a new assembly. Thereafter, 
prior to the accumulation of 4,000 landings on the jack pivot 
assembly, replace it with a new assembly in accordance with the 
service bulletin.
    (3) For sidestay assemblies that have accumulated less than 
4,000 total landings since new: Accomplish paragraphs (d)(3)(i) and 
(d)(3)(ii) of this AD.
    (i) Repeat the inspection required by paragraph (a) of this AD 
thereafter at intervals not to exceed 100 landings.
    (ii) Prior to the accumulation of 4,000 total landings on the 
jack pivot assembly, or within 300 landings after the effective date 
of this AD, whichever occurs later, replace the jack pivot assembly 
with a new assembly. Thereafter, prior to the accumulation of 4,000 
landings on the jack pivot assembly, replace it with a new assembly 
in accordance with the service bulletin.
    (e) If, during any inspection required by this AD, any crack is 
found that exceeds the limits specified in paragraph 2.B.(6)(c) of 
the Accomplishment Instructions of Raytheon Corporate Jets Service 
Bulletin SB 32-233, dated June 24, 1994: Prior to further flight, 
replace the cracked pivot assembly with a new assembly in accordance 
with the service bulletin. Thereafter, prior to the accumulation of 
4,000 landings on the jack pivot assembly, replace it with a new 
assembly in accordance with the service bulletin.
    (f) 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, Standardization Branch, ANM-113, 
FAA, Transport Airplane Directorate. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, 
Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (g) 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.
    (h) The inspections and replacements shall be done in accordance 
with Raytheon Corporate Jets Service Bulletin SB 32-233, dated June 
24, 1994. This incorporation by reference was approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Copies may be obtained from Raytheon Corporate 
Jets, Inc., 3 Bishops Square Street, Albans Road West, Hatfield, 
Hertfordshire, AL109NE, United Kingdom. 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.
    (i) This amendment becomes effective on February 3, 1995.

    Issued in Renton, Washington, on December 21, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-50 Filed 1-3-95; 8:45 am]
BILLING CODE 4910-13-U