[Federal Register Volume 63, Number 218 (Thursday, November 12, 1998)]
[Rules and Regulations]
[Pages 63137-63139]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-30048]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-72-AD; Amendment 39-10876; AD 98-23-10]
RIN 2120-AA64


Airworthiness Directives; Burkhart GROB Luft-und Raumfahrt GmbH 
Model G 109B Gliders

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to all Burkhart GROB Luft-und Raumfahrt GmbH (Grob) Model G 
109B gliders. This AD requires inspecting the engine mounting frame for 
paint scratches and damage (abrasions, notches, or chafing); and 
repairing any paint scratches, and repairing or replacing any engine 
mounting frame that is found damaged. This AD is the result of 
mandatory continuing airworthiness information (MCAI) issued by the 
airworthiness authority for Germany. The actions specified by this AD 
are intended to detect and correct damage to the engine mounting frame, 
which could result in failure of the engine mount structure with 
consequent loss of the engine.

DATES: Effective December 17, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 17, 1998.

ADDRESSES: Service information that applies to this AD may be obtained 
from Grob-Werke GmbH & Co. KG, Unternehmensbereich, Burkhart Grob 
Flugzeugbau, Flugplatz Mattsies, 86874 Tussenhausen, Germany. This 
information may also be examined at the Federal Aviation Administration 
(FAA), Central Region, Office of the Regional Counsel, Attention: Rules 
Docket No. 98-CE-72-AD, Room 1558, 601 E. 12th Street, Kansas City, 
Missouri 64106; or at the Office of the Federal Register, 800 North 
Capitol Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr. Mike Kiesov, Aerospace Engineer, 
FAA, Small Airplane Directorate, 1201 Walnut, suite 900, Kansas City, 
Missouri 64106; telephone: (816) 426-6932; facsimile: (816) 426-2169.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to all Grob Model G 109B 
gliders was published in the Federal Register as a notice of proposed 
rulemaking (NPRM) on September 2, 1998 (63 FR 46714). The NPRM proposed 
to require inspecting the engine mounting frame for paint scratches and 
damage (abrasions, notches, or chafing); and repairing any paint 
scratches, and repairing or replacing any engine mounting frame that is 
found damaged. Accomplishment of the proposed action as specified in 
the NPRM would be in accordance with Grob Service Bulletin TM 817-45, 
dated July 27, 1995.
    The NPRM was the result of mandatory continuing airworthiness 
information (MCAI) issued by the airworthiness authority for Germany.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposed rule or the FAA's determination of the cost to the public.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. The FAA has determined that these minor 
corrections will not change the meaning of the AD and will not add any 
additional burden upon the public than was already proposed.

Cost Impact

    The FAA estimates that 29 gliders in the U.S. registry will be 
affected by the

[[Page 63138]]

inspection, that it will take approximately 2 workhours per glider to 
accomplish the inspection, and that the average labor rate is 
approximately $60 an hour. Based on these figures, the total cost 
impact of the inspection on U.S. operators is estimated to be $3,480, 
or $120 per glider.
    If damage is found on the engine mounting frame that is beyond 
certain limits specified in the service information, the FAA estimates 
that it will take approximately 13 workhours per glider to accomplish 
the repair or replacement, at an average labor rate of approximately 
$60 an hour. Parts cost $200 for repair and $750 for replacement. Based 
on these figures, the total cost impact of the repair, if necessary, is 
estimated to be $980 per glider. The total cost impact of the 
replacement, if necessary, is estimated to be $1,530 per glider.

Compliance Time of This AD

    Although damage to the engine mounting frame occurs during flight, 
this unsafe condition is not a result of the number of times the glider 
is operated. The chance of this situation occurring is the same for a 
glider with 10 hours time-in-service (TIS) as it will be for a glider 
with 500 hours TIS. For this reason, the FAA has determined that a 
compliance based on calendar time should be utilized in this AD in 
order to assure that the unsafe condition is addressed on all gliders 
in a reasonable time period.

Regulatory Impact

    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 copy of the final evaluation prepared for this 
action is contained in the Rules Docket. A copy of it may be obtained 
by contacting 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 adding a new airworthiness directive 
(AD) to read as follows:

98-23-10  Burkhart Grob Luft-und Raumfahrt GmbH: Amendment 39-10876; 
Docket No. 98-CE-72-AD.
    Applicability: Model G 109B gliders, all serial numbers, 
certificated in any category.

    Note 1: This AD applies to each glider 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 gliders 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 (g) 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 in the body of this AD, unless 
already accomplished.
    To detect and correct damage to the engine mounting frame, which 
could result in failure of the engine mount structure with 
consequent loss of the engine, accomplish the following:
    (a) Within the next 3 calendar months after the effective date 
of this AD, inspect the engine mounting frame for paint scratches 
and damage (abrasions, notches, or chafing) in accordance with the 
Action section of Grob Service Bulletin TM 817-45, dated July 27, 
1995.
    (b) If a paint scratch(es), but no damage, is found during the 
inspection required by paragraph (a) of this AD, prior to further 
flight, remove all flakes and dust from the area, degrease the tube 
and apply a protective anti-corrosion coat, and shorten the warm air 
duct or replace it if damaged. Accomplish the warm air duct 
modification or replacement in accordance with the maintenance 
manual.
    (c) If a paint scratch(es) and damage are both found during the 
inspection required by paragraph (a) of this AD, accomplish the 
following:
    (1) Prior to further flight, remove all flakes and dust from the 
area; and
    (2) Perform the actions specified in paragraph (d) or (e) of 
this AD, as applicable. Accomplish these actions at the compliance 
times specified in the applicable paragraphs.
    (d) If damage (abrasions, notches, or chafing) is found during 
the inspection required by paragraph (a) of this AD, and the damage 
is 0.7 millimeters (mm) or less in depth as specified in paragraph 
3(b) of the Action section of Grob Service Bulletin TM 817-45, dated 
July 27, 1995, prior to further flight, degrease the tube and apply 
a protective anti-corrosion coat, and shorten the warm air duct or 
replace it if damaged. Accomplish the warm air duct modification or 
replacement in accordance with the maintenance manual. Within 6 
calendar months after the inspection required by paragraph (a) of 
this AD, accomplish one of the following:
    (1) Send the engine mounting frame to the manufacturer for 
repair at the address specified in paragraph (h) of this AD and 
accomplish the warm air duct modification or replacement specified 
in paragraph (b) of this AD. Do not operate the glider until the 
part is repaired, sent back, and re-installed on the glider; or
    (2) Replace the engine mounting frame with a new part of the 
same design, or an FAA-approved part that has been inspected in 
accordance with the requirements of paragraph (a) of this AD and is 
found free of damage.
    (e) If damage (abrasions, notches, or chafing) is found during 
the inspection required by paragraph (a) of this AD, and the damage 
is more than 0.7 mm in depth as specified in paragraph 3(c) of the 
Action section of Grob Service Bulletin TM 817-45, dated July 27, 
1995, prior to further flight, accomplish one of the following:
    (1) Send the engine mounting frame to the manufacturer for 
repair at the address specified in paragraph (h) of this AD and 
accomplish the warm air duct modification or replacement specified 
in paragraph (b) of this AD. Do not operate the glider until the 
part is repaired, sent back, and re-installed on the glider; or
    (2) Replace the engine mounting frame with a new part of the 
same design, or an FAA-approved part that has been inspected in 
accordance with the requirements of paragraph (a) of this AD and is 
found free of damage. Accomplish the warm air duct modification or 
replacement specified in paragraph (b) of this AD.
    (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 glider to a location where the 
requirements of this AD can be accomplished.
    (g) An alternative method of compliance or adjustment of the 
compliance times that provides an equivalent level of safety may be 
approved by the Manager, Small Airplane Directorate, 1201 Walnut, 
suite 900, Kansas City, Missouri 64106. The request shall be

[[Page 63139]]

forwarded through an appropriate FAA Maintenance Inspector, who may 
add comments and then send it to the Manager, Small Airplane 
Directorate.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Small Airplane Directorate.

    (h) Questions or technical information related to Grob Service 
Bulletin TM 817-45, dated July 27, 1995, should be directed to Grob-
Werke GmbH & Co. KG, Unternehmensbereich, Burkhart Grob Flugzeugbau, 
Flugplatz Mattsies, 86874 Tussenhausen, Germany. This service 
information may be examined at the FAA, Central Region, Office of 
the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, 
Missouri 64106.
    (i) The inspection required by this AD shall be done in 
accordance with Grob Service Bulletin TM 817-45, dated July 27, 
1995. 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 Grob-Werke GmbH & Co. KG, 
Unternehmensbereich, Burkhart Grob Flugzeugbau, Flugplatz Mattsies, 
86874 Tussenhausen, Germany. Copies may be inspected at the FAA, 
Central Region, Office of the Regional Counsel, Room 1558, 601 E. 
12th Street, Kansas City, Missouri, or at the Office of the Federal 
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in German AD 95-362 
Grob, dated September 27, 1995.

    (j) This amendment becomes effective on December 17, 1998.

    Issued in Kansas City, Missouri, on November 2, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-30048 Filed 11-10-98; 8:45 am]
BILLING CODE 4910-13-U