Airworthiness Directives; Raytheon Model BH.125, DH.125, and HS.125 Series Airplanes

[Federal Register Volume 65, Number 207 (Wednesday, October 25, 2000)]
[Rules and Regulations]
[Pages 63792-63793]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-27120]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-345-AD; Amendment 39-11943; AD 2000-21-11]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model BH.125, DH.125, and 
HS.125 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all Raytheon Model DH.125-1A, -3A, and -400A series 
airplanes, that currently requires a one-time inspection to detect 
scoring of the upper fuselage skin around the periphery of the cockpit 
canopy blister interface, and repair, if necessary. This amendment 
expands the applicability of the existing AD to include additional 
airplanes, and requires that the actions be accomplished in accordance 
with revised service information for the newly added airplanes. This 
amendment is prompted by additional reports indicating that scoring has 
been detected on the upper fuselage skin around the periphery of the 
cockpit canopy blister interface. The actions specified by this AD are 
intended to detect and correct scoring of the upper fuselage skin 
around the periphery of the cockpit canopy blister interface, which 
could result in reduced structural integrity of the fuselage, and 
consequent cabin depressurization.

DATES: Effective November 29, 2000.
    The incorporation by reference of Raytheon Aircraft Service 
Bulletin SB 53-93, Revision 2, dated April 2000, as listed in the 
regulations, is approved by the Director of the Federal Register as of 
November 29, 2000.
    The incorporation by reference of Raytheon Aircraft Service 
Bulletin SB 53-93, dated May 16, 1996, as listed in the regulations, 
was approved previously by the Director of the Federal Register as of 
June 6, 1997 (62 FR 24013, May 2, 1997).

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Aircraft Company, Commercial Service Department, 
P.O. 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, Mid-Continent Airport, Wichita, Kansas; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: T.N. Baktha, Aerospace Engineer, 
Airframe Branch, ACE-118W, FAA, Wichita Aircraft Certification Office, 
1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 
67209; telephone (316) 946-4155; fax (316) 946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 97-09-12, 
amendment 39-10008 (62 FR 24013, May 2, 1997), which is applicable to 
all Raytheon Model DH.125-1A, -3A, and -400A series airplanes, was 
published in the Federal Register on June 16, 2000 (65 FR 37723). The 
action proposed to continue to require a one-time inspection to detect 
scoring of the upper fuselage skin around the periphery of the cockpit 
canopy blister interface, and repair, if necessary. The action also 
proposed to expand the applicability of the existing AD to include 
additional airplanes and to require that the actions be accomplished in 
accordance with revised service information for the newly added 
airplanes.

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.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 290 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 200 airplanes of U.S. registry 
will be affected by this AD.
    The actions that are currently required by AD 97-09-12 and retained 
in this AD take approximately 4 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 $48,000, or $240 per airplane.
    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.

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.

[[Page 63793]]

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-10008 (62 FR 
24013, May 2, 1997), and by adding a new airworthiness directive (AD), 
amendment 39-11943, to read as follows:

2000-21-11  Raytheon Aircraft Company: Amendment 39-11943. Docket 
99-NM-345-AD. Supersedes AD 97-09-12, Amendment 39-10008.

    Applicability: Model DH.125, BH.125, and HS.125 series 
airplanes, as listed in Raytheon Aircraft Service Bulletin SB 53-93, 
Revision 2, dated April 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 detect and correct scoring of the upper fuselage skin around 
the periphery of the cockpit canopy blister interface, which could 
result in reduced structural integrity of the fuselage skin, and 
consequent cabin depressurization; accomplish the following:

Restatement of the Requirements of AD 97-09-12:

    (a) For Model DH.125-1A, -3A, and -400A series airplanes, as 
identified in Raytheon Aircraft Service Bulletin SB 53-93, dated May 
16, 1996: Within 90 days after June 6, 1997 (the effective date of 
AD 97-09-12, amendment 39-10008), perform a one-time detailed visual 
inspection to detect scoring of the upper fuselage skin around the 
periphery of the cockpit canopy blister interface, in accordance 
with the service bulletin.
    (b) If no scoring is detected during the inspection required by 
paragraph (a) of this AD, no further action is required by this AD.
    (c) If any scoring is detected during the inspection required by 
paragraph (a) of this AD, prior to further flight, determine the 
maximum location and details of each score, including the edge 
distance and material thickness, in accordance with Raytheon 
Aircraft Service Bulletin SB 53-93, dated May 16, 1996.
    (1) If any scoring is found that is within the limits specified 
in the service bulletin, prior to further flight, repair in 
accordance with the service bulletin.
    (2) If any scoring is found that is outside the limits specified 
in the service bulletin, prior to further flight, repair in 
accordance with a method approved by the Manager, Wichita Aircraft 
Certification Office (ACO), FAA.

New Requirements of this AD:

    (d) For airplanes identified in Raytheon Aircraft Service 
Bulletin SB 53-93, Revision 2, dated April 2000, and not previously 
identified in paragraph (a) of this AD: Within 90 days after the 
effective date of this AD, perform a one-time detailed visual 
inspection to detect scoring of the upper fuselage skin around the 
periphery of the cockpit canopy blister interface, in accordance 
with Raytheon Aircraft Service Bulletin SB 53-93, Revision 2, dated 
April 2000.
    (1) If no scoring is detected during the inspection required by 
paragraph (d) of this AD, no further action is required by this AD.
    (2) If any scoring is detected during the inspection required by 
paragraph (d) of this AD, prior to further flight, determine the 
location and details of each score, including the edge distance and 
material thickness, in accordance with the service bulletin.
    (i) If any scoring is found that is within the limits specified 
in the service bulletin, prior to further flight, repair in 
accordance with the service bulletin.
    (ii) If any scoring is found that is outside the limits 
specified in the service bulletin, prior to further flight, repair 
in accordance with a method approved by the Manager, Wichita ACO.

    Note 2: Any inspections and repairs accomplished prior to the 
effective date in accordance with Raytheon Service Bulletin SB 53-
93, Revision 1, dated April 1999, are considered acceptable for 
compliance for the applicable actions required by this AD.

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 ACO. 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 
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

    (g) Except as provided by paragraphs (c)(2) and (d)(2)(ii) of 
this AD, the actions shall be done in accordance with Raytheon 
Aircraft Service Bulletin SB 53-93, dated May 16, 1996; and Raytheon 
Aircraft Service Bulletin SB 53-93, Revision 2, dated April 2000; as 
applicable.
    (1) The incorporation by reference of Raytheon Aircraft Service 
Bulletin SB 53-93, Revision 2, dated April 2000, is approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51.
    (2) The incorporation by reference of Raytheon Aircraft Service 
Bulletin SB 53-93, dated May 16, 1996, was approved previously by 
the Director of the Federal Register as of June 6, 1997 (62 FR 
24013, May 2, 1997).
    (3) Copies may be obtained from Raytheon Aircraft Company, 
Commercial Service Department, 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 November 29, 2000.

    Issued in Renton, Washington, on October 17, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-27120 Filed 10-24-00; 8:45 am]
BILLING CODE 4910-13-U

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